Altitude Patents (Class 340/970)
  • Patent number: 10417918
    Abstract: A method to assist in a search and rescue mission comprises: scanning at least a portion of a terrain at a search and rescue site using a scanning device to obtain searched area information, wherein searched area information is information captured by the scanning device of the at least a portion of the terrain; analyzing the searched area information obtained after scanning the at least a portion of the terrain; and communicating leading air vehicle information to at least one trailing air vehicle, wherein leading air vehicle information includes searched area information and analysis, and wherein the at least one trailing air vehicle is an air vehicle that reaches the search and rescue site after the at least one leading air vehicle.
    Type: Grant
    Filed: January 20, 2016
    Date of Patent: September 17, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Mahipal Reddy, Anil Kumar Songa, Bharath Sundararajan
  • Patent number: 10388049
    Abstract: Avionic display systems and methods are provided for generating avionic displays including aerial firefighting symbology, which enhance pilot situational awareness and decision during aerial firefighting operations. In an embodiment, the avionic display system includes an avionic display device, a thermal image sensor configured to detect thermal image data external to the aircraft, and a controller operably coupled to the avionic display device and to the thermal image sensor. During operation of the avionic display system, the controller compiles a fire map of a fire-affected area in proximity of the aircraft based, at least in part, on the thermal image data collected by the thermal image sensor. The controller further generates a first avionic display on the avionic display device including graphics representative of a field of view (FOV) of the thermal image sensor and portions of the fire map outside of the FOV of the thermal image sensor.
    Type: Grant
    Filed: April 6, 2017
    Date of Patent: August 20, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Anil Kumar Songa, Mallikarjuna Narala, Sudheer B M, Suvankar Manna
  • Patent number: 10311737
    Abstract: Various navigation and other instrumentation systems may benefit from appropriate methods for selection of traffic. For example, certain avionics may benefit from systems and methods for selecting and designating ADS-B or similar traffic. An apparatus can include a display and a processor. The processor and the display can be configured to permit selection of at least one target aircraft identified on the display.
    Type: Grant
    Filed: October 17, 2016
    Date of Patent: June 4, 2019
    Assignee: AVIATION COMMUNICATION & SURVEILLANCE SYSTEMS LLC
    Inventors: Charles Manberg, Richard Ridenour, II
  • Patent number: 10247821
    Abstract: A weather radar system for an aircraft includes a weather radar system and a processing circuit. The weather radar system is configured to determine weather data, the weather data including an indication of precipitation at a plurality of altitudes, a plurality of azimuth angles, and at a plurality of ranges from the aircraft. The processing circuit is configured to receive the weather data from the weather radar system and generate an overhead display from an overhead perspective based on the weather data. The overhead display visually illustrates the precipitation at a particular distance from the aircraft and at a particular azimuth angle. The processing circuit is configured to generate a face-on on display based on the weather data and cause a display screen to display the overhead display and the face-on display. The face-on display visually illustrates a particular altitude of the precipitation and the azimuth angle of the precipitation.
    Type: Grant
    Filed: August 4, 2017
    Date of Patent: April 2, 2019
    Assignee: ROCKWELL COLLINS, INC.
    Inventors: Keith A. Stover, Eric N. Anderson
  • Patent number: 10126745
    Abstract: An aerial system, preferably including one or more proximity sensors, such as sensors arranged in opposing directions. A method for aerial system operation, preferably including: determining a set of sensors; sampling measurements at the set of sensors; localizing the aerial system based on the measurements, such as to determine one or more obstacle clearances; and controlling system flight, such as based on the clearances.
    Type: Grant
    Filed: November 13, 2017
    Date of Patent: November 13, 2018
    Assignee: Hangzhou Zero Zero Technology Co., Ltd.
    Inventors: Zheng Qu, Pengxiang Jin, Tong Zhang
  • Patent number: 10049588
    Abstract: A computer system 20 provided in an aircraft 1 includes, as a module of a computer program to be executed, an approach determination section 31 configured to determine whether the aircraft 1 is approaching a landing site. The approach determination section 31 includes, as a condition for determination of approaching, establishment (C1) of one or both of a condition (C11) that a first absolute altitude A1 obtained by an radio altimeter 21 mounted on the aircraft 1 is low relative to a first approach altitude AA1, and a condition (C12) that a second absolute altitude A2 that is obtained by subtracting an altitude AL of the landing site from a pressure altitude Ap determined by a barometric altimeter 22 mounted on the aircraft 1 is low relative to a predetermined second approach altitude AA2.
    Type: Grant
    Filed: August 4, 2016
    Date of Patent: August 14, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Tomoka Mashio, Kotaro Tomida
  • Patent number: 10006781
    Abstract: A method for three-dimensional graphic representation of the outside landscape in an on-board display system for aircraft comprises a graphical computer and a display screen. The graphic representation is computed to a visibility distance. In the method the zero pitch line of the aircraft forms, with the real horizon line, a first angle, the line representing the limit of the visibility distance forming, with the real horizon line, a second angle, in a first step, the graphical computer determines the maximum visibility distance such that the difference between the first angle and the second angle remains less than a determined value; in a second step, the graphical computer determines the visibility distance as a function of the maximum visibility distance, of the maximum altitude of the relief of the local environment and of the flight phase.
    Type: Grant
    Filed: June 29, 2017
    Date of Patent: June 26, 2018
    Assignee: THALES
    Inventors: Emmanuel Monvoisin, Xavier Servantie, Pierre Mariani
  • Patent number: 9751636
    Abstract: The embodiments described herein relate to dynamically detecting landing gear deployment of an aerial vehicle. A set of flight measurements is dynamically generated and stored. The set of measurements may include altitude, distance to a destination, and airspeed. Each of these measurements is compared to a respective threshold value to produce a landing scenario indication. The comparison includes ascertaining that the vehicle is within a defined above ground level based on the altitude measurement, ascertaining that the vehicle is within a defined distance to a destination based on the distance to a destination measurement, and ascertaining that the airspeed measurement is below a maximum gear extension speed. The produced indication is converted into a landing gear protocol.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: September 5, 2017
    Assignee: International Business Machines Corporation
    Inventors: John R. Dangler, David T. Nelson
  • Patent number: 9633567
    Abstract: The present invention is a system and method for aircraft ground collision avoidance (iGCAS) comprising a modular array of software, including a sense own state module configured to gather data to compute trajectory, a sense terrain module including a digital terrain map (DTM) and map manger routine to store and retrieve terrain elevations, a predict collision threat module configured to generate an elevation profile corresponding to the terrain under the trajectory computed by said sense own state module, a predict avoidance trajectory module configured to simulate avoidance maneuvers ahead of the aircraft, a determine need to avoid module configured to determine which avoidance maneuver should be used, when it should be initiated, and when it should be terminated, a notify Module configured to display each maneuver's viability to the pilot by a colored GUI, a pilot controls module configured to turn the system on and off, and an avoid module configured to define how an aircraft will perform avoidance maneuv
    Type: Grant
    Filed: December 4, 2014
    Date of Patent: April 25, 2017
    Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Mark A Skoog, Kevin Prosser, Loyd Hook
  • Patent number: 9625271
    Abstract: A method according to an aspect of the present invention includes determining if terrain presents a hazard to an aircraft based on the current position of the aircraft and the intended flight plan for the aircraft and providing an alert if it is determined that the terrain presents a hazard to the aircraft. The method may be employed in any situation to achieve any result, such as when the aircraft is in a low-RNP environment to prevent nuisance terrain alerts.
    Type: Grant
    Filed: March 4, 2008
    Date of Patent: April 18, 2017
    Assignee: AVIATION COMMUNICATION & SURVEILLANCE SYSTEMS LLC
    Inventor: Richard Darrell Ridenour, II
  • Patent number: 9557176
    Abstract: The general field of the invention is that of methods for three-dimensional conformal representation of a terrain. The method is used in a piloting and navigation assistance system of an aircraft. The assistance system comprises a navigation system, a cartographic database, electronic calculation means a meteorological database and a display system allowing the superimposition of synthetic images on the exterior. The method comprises the following steps: Step 1: Calculation, for a determined position of the vehicle, of the terrain perceptible through the display system; Step 2: Selection of a part of the said terrain as a function of a distance or of an altitude or of a range of altitudes; Step 3: Calculation of a three-dimensional conformal cartographic representation of the said selected part of the terrain; and Step 4: Display of the said cartographic representation by the display system.
    Type: Grant
    Filed: September 5, 2014
    Date of Patent: January 31, 2017
    Assignee: Thales
    Inventors: Xavier Servantie, Siegfried Rouzes, Emmanuel Monvoisin
  • Patent number: 9522742
    Abstract: A method can include determining that an aircraft is on approach to a runway. The method can include determining a flight path vector (FPV) location of the aircraft based at least in part on a projected landing location with respect to the runway and determining a current airspeed of the aircraft. The method can also include performing at least one of the following: issuing a landing short alert to a pilot of the aircraft if the FPV location is at or before the runway threshold, issuing an airspeed caution alert if the FPV location is between the runway threshold and the target runway location and if the current airspeed is below a landing short envelope, and determining not to issue an alert if the FPV location is between the runway threshold and the target runway location and if the current airspeed is at or above the landing short envelope.
    Type: Grant
    Filed: March 18, 2014
    Date of Patent: December 20, 2016
    Assignee: The Boeing Company
    Inventor: Mark Hall Henderson
  • Patent number: 9396662
    Abstract: This method of determining the risks of collision of an aircraft (1) when travelling on the ground comprises the steps of: determining the path of at least one of several parts to protect of the aircraft (1), determining a protection volume (VR, VP) associated with said at least one of several parts to protect of the aircraft, in which the shape in a horizontal plane of said protection volume depends on said path of said at least one of several parts to protect, detecting an object entering said protection volume, and generating a warning in response to detecting said object.
    Type: Grant
    Filed: March 24, 2014
    Date of Patent: July 19, 2016
    Assignee: Airbus Operations (SAS)
    Inventors: Fabrice Bousquet, Guillaume Le Berre
  • Patent number: 9390556
    Abstract: A polygonal mesh is generated from a collection of points that are organized for a mesh partition in accordance with a tile that includes one or more bins used to process the points that define the mesh. The resolution of the tile is related to the number of bins for the tile. The organization of the tiles in a partition of the mesh permits the mesh to be constructed with partitions that are independent of each other and that can be joined to form a continuous mesh. The resolution of the mesh can be dynamic with respect to the partitions due to the variable resolution assigned to each tile. Portions of the mesh for which points are not provided can be assigned finalization points to permit a continuous mesh to be constructed.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: July 12, 2016
    Assignee: TELEDYNE CARIS, INC.
    Inventor: Mark Masry
  • Patent number: 9359087
    Abstract: A method includes receiving, at a computing device, vehicle condition data from a vehicle monitoring system of a vehicle. The method also includes analyzing the vehicle condition data based on a trigger table, and based on a determination that the vehicle condition data satisfies a particular trigger condition specified in the trigger table, adding an entry in an alert evaluation queue.
    Type: Grant
    Filed: March 21, 2014
    Date of Patent: June 7, 2016
    Assignee: The Boeing Company
    Inventors: John E. Harrison, David S. Kinney, James L. Millar, Matthew D. Smith
  • Patent number: 9285217
    Abstract: The present general inventive concept relates to methods and systems to select and display information on an avionics display screen. The systems and methods allow for the selection and display of information using knobs to highlight and select the desired information for display, eliminating the need for a cursor function. The systems and methods also provide for multiple pages and/or multiple windows or “tiles” within these pages and/or windows simultaneously on a single screen of a display, with each window, page, and/or tile being fully controlled independently when selected. The present general inventive concept also relates to systems and methods to provide multiple cues on an electronic display system altitude tape to a pilot in advance and impending approach to a predefined altitude. The present general inventive concept also relates to systems and methods to employ variable resolution topographical data based on display range for an avionics navigation display.
    Type: Grant
    Filed: January 17, 2014
    Date of Patent: March 15, 2016
    Assignee: Aspen Avionics, Inc.
    Inventors: Peter Lyons, David Berlin, William Brodegard
  • Patent number: 9212931
    Abstract: The invention relates to a method of assisting piloting an aircraft. The method is performed when the real position of a symbol for display lies outside the display limit of the screen. The symbol is representative of a parameter associated with the dynamic behavior of the aircraft (FPV, . . . ) or liable to influence said behavior (FD, . . . ). The symbol possesses two components, and the first component is to be given precedence on display over the second component. In the method, the display of the symbol depends firstly on the orthogonal projection (FPV-lock) of the real position (FPV) of the symbol onto the axis of the first component, and secondly on the position of said projection relative to the display limit of the screen. Such a display makes it possible to give reliable information to the pilot.
    Type: Grant
    Filed: February 5, 2014
    Date of Patent: December 15, 2015
    Assignee: Airbus Operations (SAS)
    Inventors: David Bideau, Mathieu Rustin
  • Patent number: 9147285
    Abstract: A system for visualization of 3D objects and/or 3D terrain includes a processor, a display in communication with the processor, and a range metering device in communication with the processor. The system visualizes the 3D objects and/or the 3D terrain based upon their respective distances from the mobile device and based upon a respective parameter measuring the detail of the 3D object and/or the 3D terrain.
    Type: Grant
    Filed: August 1, 2012
    Date of Patent: September 29, 2015
    Assignee: HARMAN BECKER AUTOMOTIVE SYSTEMS GMBH
    Inventors: Peter Kunath, Alexey Pryakhin, Marek Strassenburg-Kleciak, Thomas Feldbauer, Vladimir Ivanov
  • Patent number: 9135823
    Abstract: An object type determination apparatus mounted in a vehicle. In the apparatus, a detection unit detects an object present forward of the vehicle. A height estimation unit estimates a height of the object detected by the detection unit from a road surface. A determination unit uses the estimation result of the height estimation unit to determine, according to one of a plurality of predefined criteria, whether or not the object is an object for which a collision avoidance process is performed. A complex environment estimation unit estimates a likelihood that a complex environment is present forward of the vehicle. A criterion selection unit selects the one of the plurality of predefined criteria used by the determination unit on the basis of the estimation result of the complex environment estimation unit.
    Type: Grant
    Filed: November 15, 2013
    Date of Patent: September 15, 2015
    Assignee: DENSO CORPORATION
    Inventor: Ryo Takaki
  • Patent number: 9020681
    Abstract: A method of displaying navigation limits for a planned travel route of a vehicle is presented here. The method calculates estimated navigation limits for the vehicle using an onboard subsystem of the vehicle, where the estimated navigation limits represent self-assessed navigation accuracy of the vehicle relative to the planned travel route. Contracted navigation limits are acquired for the vehicle, where the contracted navigation limits represent specified navigation accuracy of the vehicle, relative to the planned travel route, as mandated by a third party navigation controller. A navigation display is rendered on an onboard display element such that it includes graphical representations of the planned travel route, at least one of the estimated navigation limits, and at least one of the contracted navigation limits.
    Type: Grant
    Filed: June 8, 2010
    Date of Patent: April 28, 2015
    Assignee: Honeywell International Inc.
    Inventors: Petr Krupansky, Jiri Vasek, Pavel Kolcarek, Tomas Neuzil, John A. Wise
  • Patent number: 8981969
    Abstract: The invention relates to an alarm apparatus (1) for a pilot's headset (3) and to a pilot's headset having such an alarm apparatus. The alarm apparatus comprises an attitude sensor (11), which detects its inclination relative to a starting position or the horizontal, and a measuring device (12) for recording a period for which the inclination recorded by the attitude sensor exceeds a stipulated inclination tolerance limit. In addition, the alarm apparatus has a means (13) which is set up to trigger an alarm signal when a recorded period of the inclination tolerance limit being exceeded is longer than a preset maximum period.
    Type: Grant
    Filed: December 28, 2012
    Date of Patent: March 17, 2015
    Assignee: Robert Bosch GmbH
    Inventor: Martin Steinmetz
  • Patent number: 8941507
    Abstract: An flight-safe indicator for a battery displays the flight-safety state of a battery to be transported by an aircraft. The indicator can be easily recognized by ground personnel anywhere regardless of the language they speak or read. The indicator comprises an icon indicating that the battery is safe for flight and would be easily recognized by personnel at an airport. The icon would be placed on the battery or on the battery packaging prior to loading on the aircraft. When the magnitude of power stored on the battery exceeds a safety threshold, the icon changes to an indication that the battery is not safe for transporting by aircraft and the operator may discharge the battery using a load until it reaches a safe level.
    Type: Grant
    Filed: November 16, 2010
    Date of Patent: January 27, 2015
    Assignee: Panacis Inc.
    Inventor: Steve Carkner
  • Patent number: 8924137
    Abstract: According to aspects of the embodiments, there is provided an apparatus and method to synchronize trajectories from independent systems such as from a flight management system and the ground Air traffic control during the entire history of a flight. Since a number of trajectory discrepancy factors will intervene during the lifetime of a flight, such as a change in flight intent, controller intervention, or large deviations of the actual flight from the predicted trajectory due to prediction errors, there is need to dynamically monitor these deviations and control a dynamic synchronization cycle. A dynamic trajectory synchronization algorithm attempts to bring each of the systems back into balance whenever a disturbance causes an imbalance.
    Type: Grant
    Filed: September 14, 2012
    Date of Patent: December 30, 2014
    Assignee: Lockheed Martin Corporation
    Inventors: David So Keung Chan, Joel Klooster, Sergio Torres
  • Publication number: 20140354455
    Abstract: A system and method are provided for increasing vertical situational awareness when the display of intruder aircraft on a vertical situation display (VSD) is restricted to a specific region of the VSD as determined by an altitude filter. The method comprises displaying a first altitude filter limit line on the VSD.
    Type: Application
    Filed: May 31, 2013
    Publication date: December 4, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Subash Samuthirapandian, Markus Alan Johnson, Ronald Brian Wayman
  • Patent number: 8874311
    Abstract: A method and apparatus for managing a programmable control panel for a vehicle. A number of first level control functions is assigned to the programmable control panel for the vehicle. A number of second level control functions is assigned to the programmable control panel based on a health of programmable control panels in the vehicle.
    Type: Grant
    Filed: November 16, 2011
    Date of Patent: October 28, 2014
    Assignee: The Boeing Company
    Inventors: Ty Aaby Larsen, Emma Romig
  • Patent number: 8773299
    Abstract: An exemplary embodiment relates to an aircraft system for detecting wires. The system includes a processor configured to actively sense a presence of a first object and a second object. The processor determines a location of the first object and the second object. The processor determines a potential location of a wire between the first object and the second object. The processor actively senses the wire by providing electromagnetic energy to the potential location.
    Type: Grant
    Filed: September 29, 2009
    Date of Patent: July 8, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: Daniel L. Woodell, Richard D. Jinkins, Richard M. Rademaker
  • 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: 8755954
    Abstract: A system and methods for generating alerts in a terrain awareness and warning system (“TAWS”) in an aircraft, using data acquired from a forward-looking radar The system comprises a forward-looking imaging device, an airport database, a navigation system, a forward-looking terrain alert (“FLTA”) processor, and a crew alerting system. The FLTA processor determines a measured clearance altitude of a highest cell within an area and compares it with a required minimum clearance altitude; if the measured altitude is equal or less than the required altitude, the crew is alerted. Alternatively, a terrain database may be used. with the FLTA processor for determining if the aircraft descends below the minimum operating altitude or is predicted to do so and then generating an alert. A method is disclosed for generating TAWS alerts using elevation angle measured by the forward-looking radar and terrain data retrieved from a terrain database.
    Type: Grant
    Filed: September 27, 2007
    Date of Patent: June 17, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: Patrick D. McCusker, Joel M. Wichgers, Richard D. Jinkins, Richard M. Rademaker, Daniel L. Woodell
  • Patent number: 8723686
    Abstract: A method of managing an aircraft in flight may include electronically monitoring for a presence of a threat object along a flight path of the aircraft and at a destination airport of the aircraft, and electronically generating an alert when the presence of the threat object is detected. The alert may include information enabling air traffic control (ATC), flight dispatch, and a pilot of the aircraft to make a collaborative flight path correction decision that may prevent the aircraft from being affected by the threat object.
    Type: Grant
    Filed: July 31, 2012
    Date of Patent: May 13, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: Gregory D. Murray, Kirschen A. Seah, Alan E. Siniff
  • Patent number: 8723694
    Abstract: A hazard detection system is for use on board an aircraft or other vehicle. The aircraft or other vehicle is disposed in an environment. The hazard detection system includes a circuit for receiving a charge accumulation signal indicative of the electric field associated with the environment. The circuit provides a warning in response to the charge accumulation signal. The warning is indicative of a hazard or potential hazard.
    Type: Grant
    Filed: September 16, 2010
    Date of Patent: May 13, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: Jeffery A. Finley, Terrence P. Wey, Kevin M. Kronfeld, Gregory J. Koenigs
  • Patent number: 8723695
    Abstract: A method for automatically detecting an erroneous height value supplied by a radio altimeter mounted on an aircraft. The method includes measuring, during the aircraft's approach phase with a view to landing, the duration between the times when a first predetermined altitude threshold and a second predetermined altitude threshold are reached. This duration is measured by taking into account current height values supplied by the radio altimeter. The method then includes comparing the measured duration to a predetermined duration reference time, which is lower than a flight duration that would allow the aircraft to descend from the first predetermined altitude threshold to the second predetermined altitude threshold at a maximum vertical speed. An erroneous height value is detected if the measured duration is lower than the predetermined duration reference time.
    Type: Grant
    Filed: August 15, 2011
    Date of Patent: May 13, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Thierry Bourret, Pierre-Antoine Lierman
  • Patent number: 8681021
    Abstract: Present novel and non-trivial system, apparatus, and method for generating a lateral meteorological profile are disclosed. The system is comprised of a source for providing hazard data and a lateral profile generator (“LPG”), where the source could be comprised of an aircraft weather system and/or a datalink system through which hazard weather data is received. The apparatus is comprised of the LPG configured to perform the method comprised of receiving hazard data, determining profile location data, and generating profile image data. The hazard data represents location information of each hazard located outside the aircraft, the profile location data is representative of a plurality of locations of maximum vertical sector height within a vertical sector, and the profile image data is representative of a lateral meteorological profile comprised of a plurality of points, each point corresponding to one location of the maximum vertical sector height.
    Type: Grant
    Filed: September 29, 2011
    Date of Patent: March 25, 2014
    Assignee: Rockwell Collins, Inc.
    Inventor: Matthew J. Carrico
  • Publication number: 20140074324
    Abstract: Methods and systems are provided for displaying visually distinguishing characteristics if an aircraft is below a minimum altitude or beyond a maximum distance when executing a procedure turn. A procedure turn icon, an aircraft icon indicating the aircraft's present location, terrain/obstacles, and the visually distinguishing characteristics are displayed on a moving map.
    Type: Application
    Filed: September 12, 2012
    Publication date: March 13, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Roger W. Burgin, Dave Pepitone, Blake Wilson
  • Patent number: 8660716
    Abstract: Methods, systems, and computer-readable media are described herein for providing comparative vertical situation displays of multiple flight routes. According to embodiments presented herein, information regarding a currently active flight route of an aircraft and one or more proposed alternate flight routes is combined with airborne constraint data to display a comparative vertical situation display for each of the active route and/or the proposed routes. Each of the comparative vertical situation displays shows the vertical component of the corresponding flight route along with the vertical components of one or more airborne constraints along the corresponding flight route. The comparative vertical situation displays are concurrently shown on a display unit, allowing the flight crew of the aircraft or route planning personnel to compare the impact of the airborne constraints along the vertical component of each of the flight routes.
    Type: Grant
    Filed: May 3, 2010
    Date of Patent: February 25, 2014
    Assignee: The Boeing Company
    Inventors: Timothy F. Rahmes, Peter James Batsakes
  • Patent number: 8643508
    Abstract: The present general inventive concept relates to methods and systems to select and display information on an avionics display screen. The systems and methods allow for the selection and display of information using knobs to highlight and select the desired information for display, eliminating the need for a cursor function. The systems and methods also provide for multiple pages and/or multiple windows or “tiles” within these pages and/or windows simultaneously on a single screen of a display, with each window, page, and/or tile being fully controlled independently when selected. The present general inventive concept also relates to systems and methods to provide multiple cues on an electronic display system altitude tape to a pilot in advance and impending approach to a predefined altitude. The present general inventive concept also relates to systems and methods to employ variable resolution topographical data based on display range for an avionics navigation display.
    Type: Grant
    Filed: July 26, 2010
    Date of Patent: February 4, 2014
    Assignee: Aspen Avionics, Inc.
    Inventor: Brian Turner
  • Patent number: 8576093
    Abstract: The invention relates to an aircraft navigational aid system with 3D display including an anti-collision device, with means of storing data representing obstructions, means for calculating a representation of the obstructions in a three-dimensional space and a device for displaying the obstructions data in three dimensions. The system includes means for augmenting the display of the representation of the area of hazardous obstructions with at least two indicator objects for the said area of hazardous obstructions disposed together in such a manner as to form a third object targeting the localization of the point in the area of hazardous obstructions closest to the aircraft. The invention also relates to the method of display of the indicator objects in a three-dimensional display.
    Type: Grant
    Filed: August 27, 2010
    Date of Patent: November 5, 2013
    Assignee: Thales
    Inventors: Laurent Flotte, Gabrielle DeBrito, Christian Nouvel, Nicolas Marty
  • 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: 8547252
    Abstract: A method of generating a terrain avoidance warning for a rotary wing aircraft including generating an avoidance trajectory including a proximal segment representative of a transfer time and an avoidance curve including at least one distal segment of a conic section curve following on from the proximal segment, wherein the proximal segment extends in continuation from a predicted trajectory over a distance representing an applicable reaction time, the applicable reaction time being minimized as a function of a route sheet for the aircraft, and wherein the generating includes calculating the at least one distal segment as a function of an instantaneous maneuverability of the aircraft.
    Type: Grant
    Filed: June 22, 2009
    Date of Patent: October 1, 2013
    Assignee: Eurocopter
    Inventors: Serge Germanetti, Alain Ducollet
  • Patent number: 8514102
    Abstract: An aircraft display system is provided for rendering at least aircraft estimated position uncertainty (EPU) and/or vertical estimated position uncertainty (VEPU) values non-numerically and in a fairly intuitive manner. The system may also render the EPU and VEPU values non-numerically for other traffic entities within range of the aircraft.
    Type: Grant
    Filed: January 14, 2010
    Date of Patent: August 20, 2013
    Assignee: Honeywell International Inc.
    Inventors: Dhivagar Palanisamy, Haricharan Reddy, Vishnu Vardhan Reddy Annapureddy, Saravanakumar Gurusamy, Santhosh Gautham
  • Patent number: 8502702
    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: Grant
    Filed: July 26, 2010
    Date of Patent: August 6, 2013
    Assignee: Aspen Avionics, Inc.
    Inventors: Peter Lyons, Jeffrey D. Bethel
  • Patent number: 8494693
    Abstract: A monitor on-board an aircraft which uses radio altitude measurements as the basic observable altitude during runway approach. The basic concept utilizes the aircraft's navigation system, which includes means to store and retrieve radio altitude thresholds as a function of the distance along the desired path from the runway thresholds. These threshold functions are determined in advance based on a radio altitude reference which is defined as the expected radio altimeter measurement that would be made if the airplane were exactly on the desired reference path. Vertical containment monitoring is achieved by comparing the radio altitude measurement to computed thresholds for both too high and too low. During the approach, an annunciation message can be generated if the radio altitude measurement is above or below the threshold limits.
    Type: Grant
    Filed: August 5, 2009
    Date of Patent: July 23, 2013
    Assignee: The Boeing Company
    Inventor: Timothy Allen Murphy
  • Patent number: 8477048
    Abstract: According to the invention, the device (1) comprises means (3) for detecting, during an altitude capture maneuver, the emission of a first type alarm by the anti-collision system (2) and means (4) for controlling the vertical speed of said airplane (AC), after the emission of such an alarm, until the triggering of the capture phase.
    Type: Grant
    Filed: January 28, 2011
    Date of Patent: July 2, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Paule Botargues, Xavier Dal Santo, Olivier Sapin, Vincent Bompart
  • Patent number: 8463463
    Abstract: Methods for flying multiple aircraft in a predetermined formation in which a relative navigation grid is emitted from at least one of the aircraft, a spatial relationship is calculated based on the emitted relative navigation grid, and a relative position of at least one aircraft is altered to position the aircraft in the predetermined formation when the spatial relationship does not conform with the predetermined formation.
    Type: Grant
    Filed: February 27, 2012
    Date of Patent: June 11, 2013
    Assignee: GE Aviation Systems LLC
    Inventors: Michael Steven Feldmann, Jerry Lynne Page
  • Patent number: 8446295
    Abstract: According to the invention, the device (1) comprises means (4) for adapting the altitude capture maneuver, means (5) for first detecting the emission of a first type alarm, means (6) for determining a first alarm threshold and means (7) for establishing an activation height threshold from said first alarm threshold and airplane vertical speed at the time of the alarm emission, so that, when the height separating said aircraft (AC) from the altitude set level is strictly higher than said height threshold at the time of the alarm emission, said adaptation means (4) are disabled.
    Type: Grant
    Filed: January 28, 2011
    Date of Patent: May 21, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Paule Botargues, Xavier Dal Santo, Olivier Sapin, Vincent Bompart
  • Publication number: 20130106623
    Abstract: Systems and methods for improving sink rate alerting for rotary wing aircraft. In one example, the system includes a radio altimeter that produces an altitude value, a processor that is in signal communication with the user interface device and the radio altimeter. The processor receives an altitude value, a position value for the aircraft and landing zone (LZ) information. The processor determines if the aircraft is on an approach to land at an LZ that is raised above surrounding terrain based on the received position value and LZ information. The processor receives sink rate information for the aircraft and generates a sink rate alert based on the received sink rate information and the aircraft altitude value if the sink rate information is greater than a sink rate value adjusted according to the LZ information. An output device outputs the generated sink rate alert. The LZ information includes an altitude value.
    Type: Application
    Filed: October 31, 2011
    Publication date: May 2, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Yasuo Ishihara, Steve Johnson, Gary A. Ostrom
  • Patent number: 8416100
    Abstract: A method and device performs onboard monitoring of a horizontal position of a taxiing aircraft, in which the monitoring of the horizontal position is based on separately determined height differences of the aircraft. A predetermined threshold value is compared with a first height difference calculated using repetitively determined first current height positions received by an onboard positioning device over a first duration. The predetermined threshold value is also compared with calculated second height differences calculated from two successively measured second current height positions determined by an altimeter over a second duration that is less than or equal to the first duration. A warning signal, signaling a problem with the reliability of the monitored horizontal position of the taxiing aircraft, is emitted in the event none of the second height differences is greater than the threshold value, and the first height difference is greater than the threshold value.
    Type: Grant
    Filed: May 5, 2008
    Date of Patent: April 9, 2013
    Assignee: Airbus Operations SAS
    Inventor: Laurent Azoulai
  • Patent number: 8401773
    Abstract: An air traffic control system, for use by a human controller controlling a plurality of aircraft held vertically separated in a stack above a minimum stack level, the system comprising at least one processor, and a display device for the human controller, controlled by said at least one processor; further comprising: means for periodically inputting a value representative of local terrestrial air pressure conditions; means for periodically inputting an aircraft flight level reading representing an altitude defined by a reference air pressure measured on the aircraft; means for periodically generating a display on said display device comprising a plurality of flight levels vertically arranged; means for indicating in said display said plurality of aircraft, arranged in a vertical list ranked by flight level; said at least one processor being arranged, on reception of a new said value, to redetermine said minimum stack level and to vary said display so as to indicate changes to said minimum stack level.
    Type: Grant
    Filed: June 29, 2007
    Date of Patent: March 19, 2013
    Assignee: Nats (En Route) Public Limited Company
    Inventors: Robert Eagles, Jenny Weston, William Casey, Martin Southall
  • Patent number: 8395533
    Abstract: The invention relates to a method for managing an anti-collision system for aircraft, said system comprising means of detecting collision with a threat and at least one head-up viewing device. The symbol system comprises two display modes dedicated to collision detection which are: on the one hand an “action” mode: a potential collision is detected by the system, the symbol system comprises at least one symbol representative of the limits of the disengagement path of the aircraft to avoid the collision and enabling the pilot to engage his avoidance maneuver, and on the other hand a “control” mode: this mode is displayed when the avoidance maneuver is engaged and the collision avoided, the symbol system comprises at least the symbol representative of the limits of the disengagement path of the aircraft and a plan view representing the air space around the aircraft and including at least one representation of the threat.
    Type: Grant
    Filed: August 25, 2008
    Date of Patent: March 12, 2013
    Assignee: Thales
    Inventors: Thierry Ganille, Regis Azarian, Eric Filliatre
  • Patent number: 8395534
    Abstract: A system configured for viewing meteorological data and generating said alerts in an aircraft. The system includes a navigation screen configured to display meteorological data in a monitoring plane at a determined altitude (Zs), and an altitude determination unit configured to determine the current altitude (Zp) of the aircraft. A processor is configured to determine the difference in altitude (Dz) between the aircraft's current altitude (Zp) and the altitude of the monitoring plane (Zs). The determined altitude difference (Dz) is compared with a first predetermined deviation threshold (S1), and a first alert (A1) is emitted under conditions in which the altitude difference (Dz) attains or exceeds the first predetermined deviation threshold (S1) and the altitude difference (Dz) diverges.
    Type: Grant
    Filed: October 7, 2009
    Date of Patent: March 12, 2013
    Assignee: Airbus Operations SAS
    Inventors: Laure Christophe, Garance Raynaud
  • 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