I.l.s. Or Radar Guidance Patents (Class 701/17)
  • Patent number: 11250847
    Abstract: A wireless communication system includes a smart device configured for transcribing text-to-speech (STT) for display. The smart device interfaces with a radio communications device, for example, in an aircraft (AC). The system includes a filter for optimizing STT functions. Such functions are further optimized by restricting the databases of information, including geographic locations, aircraft identifications and carrier information, whereby the database search functions are optimized. Methods for wireless communications using smart devices and STT functionality are disclosed.
    Type: Grant
    Filed: July 17, 2019
    Date of Patent: February 15, 2022
    Assignee: Appareo Systems, LLC
    Inventors: Joshua N. Gelinske, Bradley R. Thurow, Jesse S. Trana, Dakota M. Smith, Nicholas L. Butts, Jeffrey L. Johnson, Derek B. Aslakson, Jaden C. Young
  • Patent number: 10969500
    Abstract: A method for determining an azimuth angle of a wind power installation is provided. The method includes attaching at least two global navigation satellite system (GNSS) receivers to a nacelle, comparing reception signals of the GNSS receivers, deriving the azimuth angle from the comparison. The at least two GNSS receivers may be attached to a wind measuring supporting frame. Provided is a method including attaching a telescopic sight to a nacelle, determining a bearing of a bearing object at a bearing angle, deriving the azimuth angle from a comparison of the bearing angle with coordinates of the bearing object and/or the wind power installation. The telescopic sight may be attached to a wind measuring supporting frame. The at least one GNSS receiver may be attached to a wind measuring supporting frame. A wind power installation is also provided.
    Type: Grant
    Filed: December 15, 2016
    Date of Patent: April 6, 2021
    Assignee: Wobben Properties GmbH
    Inventors: Marcel Weber, Marc Jandl
  • Patent number: 10794727
    Abstract: A verification method comprising a first step of measuring at least one position parameter of an aircraft and a first set of steps implemented after the flight of at least one aircraft, in an automatic and repetitive manner, comprising computing a geographical height of an aircraft with respect to the runway on the basis of the position parameters of an aircraft, computing an evaluated vertical deviation, between the geographical height and a reference height, and computing a vertical error on the basis of a comparison between the evaluated vertical deviation and the reference vertical deviation.
    Type: Grant
    Filed: June 6, 2017
    Date of Patent: October 6, 2020
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Thierry Bourret, Nicolas Marconnet
  • Patent number: 10620640
    Abstract: An aircraft landing system is disclosed. In various embodiments, an aircraft landing system as disclosed herein includes a processor that determines to start a final stage of descent for the aircraft. The processor determines a set of commands for actuators of the aircraft, based on the determination to start the final stage of descent, to flare the aircraft while wings of the aircraft are substantially in a forward flight position followed by transitioning to a vertical tilt position and completing the landing in substantially vertical flight. The commands are provided to the actuators of the aircraft.
    Type: Grant
    Filed: July 18, 2018
    Date of Patent: April 14, 2020
    Assignee: Kitty Hawk Corporation
    Inventors: Damon Vander Lind, Gregory Mainland Horn, Thomas Van Alsenoy
  • Patent number: 10402646
    Abstract: Aerial vehicles that are equipped with one or more imaging devices may detect obstacles that are small in size, or obstacles that feature colors or textures that are consistent with colors or textures of a landing area, using pairs of images captured by the imaging devices. Disparities between pixels corresponding to points of the landing area that appear within each of a pair of the images may be determined and used to generate a reconstruction of the landing area and a difference image. If either the reconstruction or the difference image indicates the presence of one or more obstacles, a landing operation at the landing area may be aborted or an alternate landing area for the aerial vehicle may be identified accordingly.
    Type: Grant
    Filed: December 11, 2017
    Date of Patent: September 3, 2019
    Assignee: Amazon Technologies, Inc.
    Inventor: Andreas Klaus
  • Patent number: 10403153
    Abstract: An autonomous emergency flight management system may find safe and clear landing sites for unmanned aerial systems (UASs) in emergency situations. Emergency flight management software may reside on an onboard computing system. The computing system may continuously look at internal databases and input from other systems (e.g., a global positioning system (GPS), camera, compass, radar, sonar, etc.), depending on what is available. The emergency flight management system may make decisions on its own without human intervention. For instance, a database may provide some local likely candidates for landing sites. Information associated with the candidates may include latitude, longitude, altitude for top of a building, etc. Position updates may be continuously provided from an autopilot or other suitable system.
    Type: Grant
    Filed: January 3, 2017
    Date of Patent: September 3, 2019
    Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASA
    Inventors: Patricia C. Glaab, Louis J. Glaab
  • Patent number: 9547312
    Abstract: A guiding unit and a computation unit, the computation unit comprising elements for saturating, if necessary, a usual optimized slope for the landing, following a comparison with a slope computed on the basis of a performance criterion relative to a deceleration capability of the aircraft.
    Type: Grant
    Filed: January 19, 2015
    Date of Patent: January 17, 2017
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Alexandre Buisson, Benjamin Tessier
  • Patent number: 9159242
    Abstract: An electronic system with real-time fault detection is provided. In one embodiment, the system includes analog circuitry, having a first input coupled to receive an input signal and a second input coupled to receive a test signal. The test signal is at an edge of a selected band that contains the input signal. The test signal is used to identify faults in the electronic system during operation of the electronic system. The electronic system further includes an analog to digital (A/D) converter coupled to an output of the analog circuitry. The A/D converter generates digitized spectrum. Digital circuitry is coupled to the output of the A/D converter. The digital circuitry processes the input signal from the band to provide an output for the system and processes the test signal to detect faults in the analog circuitry, the digital circuitry and the A/D converter.
    Type: Grant
    Filed: July 12, 2013
    Date of Patent: October 13, 2015
    Assignee: Honeywell International Inc.
    Inventors: Alfonso Malaga, Walter Devensky
  • Patent number: 9014881
    Abstract: A system for providing a visual indication of a predicted stopping point to an aircraft crew during landing or an aborted take-off attempt includes a ground based transceiver to determine aircraft position along a runway, a processor to determine deceleration of aircraft, and a ground based visual display. The transceiver is located adjacent to the runway to capture the location of an aircraft along the runway and to convey that information to the processor. The processor continually compares the location of the aircraft on the runway to project a stopping point for the aircraft based on current conditions. The stopping point is conveyed to the crew by the ground based visual display.
    Type: Grant
    Filed: March 28, 2012
    Date of Patent: April 21, 2015
    Inventors: Louis DeGagne, Derek Campbell
  • Patent number: 8989921
    Abstract: An electronic flight control system for an aircraft capable of hovering and having at least one rotor. The flight control system is configured to operate in a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from the pilot; and in at least two automatic flight control modes corresponding to respective flight modes of the aircraft, and in which the flight control system controls rotor speed automatically on the basis of flight conditions. The flight control system is also configured to memorize, for each automatic flight control mode, a respective flight table relating different speed values of the rotor to different values of at least one flight quantity; and to automatically control rotor speed in the automatic flight control modes on the basis of the respective flight tables.
    Type: Grant
    Filed: June 10, 2010
    Date of Patent: March 24, 2015
    Assignee: Agustawestland S.p.A.
    Inventors: Fabio Nannoni, Pierre Abdel Nour, Marco Cicale′
  • Publication number: 20150081144
    Abstract: A method and device for aiding piloting of an aircraft during an approach phase for the purpose of landing. The device includes a guidance system for guiding the aircraft according to a first guidance mode during an initial phase upstream of a transition point, then guiding the aircraft according to a second guidance mode during a terminal phase between the transition point and the landing, the device further including a computing system for automatically computing the coordinates of the transition point, the guidance system also configured for automatically disabling the second guidance mode upstream of the transition point.
    Type: Application
    Filed: September 10, 2014
    Publication date: March 19, 2015
    Inventors: Jean-Damien PERRIE, Jean MULLER, Daniel ZAPATA-ARENAS, Sylvain RAYNAUD
  • Patent number: 8958932
    Abstract: Systems and methods to mitigate instrument landing system (ILS) overflight interference are disclosed. An example method performing a first measurement of a position of an aircraft relative to a first location based on an instrument landing system, performing a second measurement of the position of the aircraft based on inertial measurements performed over a first time period occurring prior to the first measurement, performing a third measurement of the position of the aircraft based on inertial measurements performed over a second time period greater than the first time period and occurring prior to the first measurement, and generating guidance information based on a selected one of the first, second, or third measurements of the position of the aircraft.
    Type: Grant
    Filed: February 11, 2013
    Date of Patent: February 17, 2015
    Assignee: The Boeing Company
    Inventor: Tim Murphy
  • Publication number: 20150032300
    Abstract: Device for determining location information, primary references consolidated for an aircraft, comprising a chain for determining location information comprising means for measuring radionavigation data, suitable means for consolidating, suitable means for computing parameters and suitable means for consolidating the parameters. The device also comprises a chain for determining inertial primary references comprising means for measuring inertial data, suitable means for consolidating, suitable means for computing parameters and suitable means for consolidating the parameters. The device finally comprises a chain for determining anemo-barometric data comprising means for measuring anemo-barometric data, suitable means for consolidating the measured anemo-barometric data, suitable means for computing parameters, and suitable means for consolidating the reference parameters.
    Type: Application
    Filed: April 5, 2013
    Publication date: January 29, 2015
    Applicant: THALES
    Inventor: THALES
  • Publication number: 20150019051
    Abstract: An electronic system with real-time fault detection is provided. In one embodiment, the system includes analog circuitry, having a first input coupled to receive an input signal and a second input coupled to receive a test signal. The test signal is at an edge of a selected band that contains the input signal. The test signal is used to identify faults in the electronic system during operation of the electronic system. The electronic system further includes an analog to digital (A/D) converter coupled to an output of the analog circuitry. The A/D converter generates digitized spectrum. Digital circuitry is coupled to the output of the A/D converter. The digital circuitry processes the input signal from the band to provide an output for the system and processes the test signal to detect faults in the analog circuitry, the digital circuitry and the A/D converter.
    Type: Application
    Filed: July 12, 2013
    Publication date: January 15, 2015
    Inventors: Alfonso Malaga, Walter Devensky
  • Patent number: 8933957
    Abstract: Methods and systems for visually organizing aviation or aeronautical charts with color emphasis and de-emphasis features selected by a user.
    Type: Grant
    Filed: August 18, 2008
    Date of Patent: January 13, 2015
    Assignee: The Boeing Company
    Inventor: Brian B. Kennedy
  • Publication number: 20140365045
    Abstract: A method having a preparation stage for preparing an approach path (25) to a theoretical position (20?) of a platform (20). During a consolidation stage, a current position (20?) of said platform (20) is determined and an alert is triggered when the distance (D1) between said theoretical position (20?) and said current position (20?) is greater than a first threshold. During a security stage, entities provided with respective automatic identification systems and present in a predetermined monitoring zone (OCZ) are monitored, and a horizontal representation of said approach path (25) is displayed on a display screen (8) together with the following for each entity: a plot (41) representing its current position; an indication (42) of the travel direction of the entity; and a representation (43) relating to the danger level of the entity.
    Type: Application
    Filed: June 3, 2014
    Publication date: December 11, 2014
    Applicant: AIRBUS HELICOPTERS
    Inventors: Nicolas CANALE, Lionel IRAUDO
  • 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: 8886373
    Abstract: The present invention relates to a system and a method for assisting in the decking of an aircraft on a platform, more particularly on a mobile platform comprising a decking surface, said aircraft comprising a signal transmitter, the system comprising means for determining flight commands to be executed by the aircraft, said means being at least fed by locating means of the aircraft and by means of predicting movements of the platform, the locating means comprising at least two passive sensors, spaced apart, fixed in proximity to the decking surface and able to receive the signals transmitted by the aircraft. The invention applies notably to the decking of rotary wing craft and autonomous aircraft on ships.
    Type: Grant
    Filed: April 2, 2010
    Date of Patent: November 11, 2014
    Assignee: Thales
    Inventors: Patrick Garrec, Pascal Cornic, Eric Barraux
  • Patent number: 8886450
    Abstract: The present invention is directed to a system and method for identifying maneuvers for a vehicle in conflict situations. A plurality of miss points are calculated for the vehicle and as well as object conditions at which the vehicle will miss an impact with the at least one other object by a range of miss distances. The miss points are displayed such that a plurality of miss points at which the vehicle would miss impact by a given miss distance indicative of a given degree of conflict is visually distinguishable from other miss points at which the vehicle would miss impact by greater miss distances indicative of a lesser degree of conflict. The resulting display indicates varying degrees of potential conflict to present, in a directional view display, a range of available maneuvers for the vehicle in accordance with varying degrees of conflict.
    Type: Grant
    Filed: February 20, 2007
    Date of Patent: November 11, 2014
    Assignee: Commonwealth Scientific and Industrial Research Organisation
    Inventors: David John Gates, Elliot Ashley Gates, Mark Westcott, Neale Leslie Fulton
  • Publication number: 20140288733
    Abstract: Systems and methods for reducing error detection latency in LPV approaches are provided. In certain embodiments, a method for navigational guidance includes calibrating inertial measurements acquired from an inertial navigation system with satellite-based augmentation system position measurements acquired from a satellite-based augmentation system to create corrected inertial navigation system positions. The method also includes determining whether the satellite-based augmentation system experienced a fault when the inertial measurements were calibrated with the satellite-based augmentation system position measurements. Further, when the satellite-based augmentation system did not experience a fault, the method includes monitoring the satellite-based augmentation system navigation position measurements based on the corrected inertial navigation system positions.
    Type: Application
    Filed: March 19, 2013
    Publication date: September 25, 2014
    Applicant: Honeywell International Inc.
    Inventors: Gang He, Ivan Sandy Wyatt
  • Publication number: 20140277857
    Abstract: Methods, systems, and computer readable media are disclosed for direct arming aircraft runway approach guidance modes, for example and without limitation, for aircraft operational. In some aspects, a method for directly arming a runway approach guidance mode of an aircraft includes displaying on a display unit an airport, selecting the airport and selecting an active runway for final approach, displaying an path toward the selected final approach runway, selecting the final approach runway, displaying on the display unit at least one symbol associated with at least one runway approach guidance mode, and arming at least one of the at least one runway approach guidance mode.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventors: Thierry BOURRET, Pascale LOUISE, Claire OLLAGNON, Nicolas CHAUVEAU, Sebastien GIULIANO, Sebastien DRIEUX
  • Publication number: 20140249703
    Abstract: Systems and methods to accurately display lateral deviation symbology in offset approaches to runways is provided. A system for on-aircraft display of lateral deviation symbology for use in offset approaches comprises means for generating a conformal video display representation of an aircraft's current position, means for notifying a flight crew of the existence of an offset approach, means for displaying an extended runway center line, and means for displaying an approach line.
    Type: Application
    Filed: May 14, 2014
    Publication date: September 4, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: Gang He
  • Patent number: 8818582
    Abstract: A method for guiding an aircraft during its final approach to a landing runway, whereby the aircraft is guided during its approach by aircraft position information obtained from an GNSS satellite navigation system, wherein: prior to the start of the final approach a first time tFAF is determined corresponding with the start of said final approach and a second time tTD corresponding with the landing of the aircraft on said runway, then a set of satellites is determined of the satellite navigation system for excluding from the calculation of said aircraft position information during at least a part of the time interval comprised between said first and second times; and during the final approach, the aircraft position information is determined while excluding the information corresponding with all the satellites of said set of satellites and the aircraft is guided along its final approach path by said position information.
    Type: Grant
    Filed: September 17, 2012
    Date of Patent: August 26, 2014
    Assignees: Airbus Operations S.A.S., Ecole Nationale de l'Aviation Civile (E.N.A.C.)
    Inventors: Pierre Neri, Laurent Azoulai, Jean Muller, Christophe Macabiau
  • Publication number: 20140229039
    Abstract: Systems and methods to mitigate instrument landing system (ILS) overflight interference are disclosed. An example method performing a first measurement of a position of an aircraft relative to a first location based on an instrument landing system, performing a second measurement of the position of the aircraft based on inertial measurements performed over a first time period occurring prior to the first measurement, performing a third measurement of the position of the aircraft based on inertial measurements performed over a second time period greater than the first time period and occurring prior to the first measurement, and generating guidance information based on a selected one of the first, second, or third measurements of the position of the aircraft.
    Type: Application
    Filed: February 11, 2013
    Publication date: August 14, 2014
    Applicant: THE BOEING COMPANY
    Inventor: THE BOEING COMPANY
  • Patent number: 8798820
    Abstract: Systems and methods for accurately converting angular localizer data into rectilinear localizer data thereby allowing for improved localizer capture performance and stability. The systems and methods utilize information onboard an aircraft regarding the aircraft's current position and the destination runway's position to more accurately determine a distance measurement for converting angular deviations into rectilinear deviations.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: August 5, 2014
    Assignee: The Boeing Company
    Inventor: Andrew Robert Hooks
  • Patent number: 8781654
    Abstract: The device includes elements of a processing unit which determine a limit trajectory representing a flight trajectory which is compatible with the aircraft performance during the approach and which shows the limits for the flight of the aircraft. For example, a vertical profile and a horizontal trajectory are determined, with the horizontal trajectory being non-linear so that the energy of the aircraft can be sufficiently dissipated before final approach along an approach axis, while also avoiding obstacles. Thus, a flight trajectory is determined even when the aircraft has deviated from a flight plan and approach axis.
    Type: Grant
    Filed: December 2, 2011
    Date of Patent: July 15, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Andrea Giovannini, Thomas Pastre
  • 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: 8712609
    Abstract: A method is provided for displaying information on a display device of an aircraft. The method comprises determining graphics data for visual aids that represent missed approach data; incorporating the graphics data into a user interface that is in perspective view; and generating the user interface for display on the display device of the aircraft.
    Type: Grant
    Filed: May 14, 2012
    Date of Patent: April 29, 2014
    Assignee: Honeywell International Inc.
    Inventors: Navin Kadavil, Anil Kumar Songa, Prashant Prabhu, Ravindra Jayaprakash, Sadguni Venkataswamy
  • Publication number: 20140100720
    Abstract: An onboard monitor that ensures the accuracy of data representing the calculated position of an airplane during final approach to a runway. This airplane position assurance monitor is a software function that uses dissimilar sources of airplane position and runway data to ensure the accuracy of the respective data from those dissimilar sources. ILS data and GPS or GPS/Baro data are the dissimilar sources of airplane position data used by this function. This function will calculate the airplane's angular deviations from the runway centerline and from the glide slope with onboard equipment and then compare those angular deviations to the ILS angular deviation information.
    Type: Application
    Filed: December 9, 2013
    Publication date: April 10, 2014
    Applicant: THE BOEING COMPANY
    Inventors: Steven L. Fleiger-Holmes, Timothy Allen Murphy, Jean Marie Crane
  • Patent number: 8682510
    Abstract: A method for determining the distance of an aircraft from an offset runway during a landing by offset approach, the offset runway being situated at a distance D from a main runway equipped with at least one elevation beacon, comprises at least the following steps: determining the height h at which the aircraft is situated, height determined with respect to a point T1 of the offset runway, height measured by a radioaltimeter with which the aircraft is equipped, determining the angle of elevation ? of the MLS mode by using the information of the elevation beacon provided by an elevation beacon with which said main runway is equipped, determining the value of the distance ? of the aircraft from the azimuth beacon (10) by using the following formula ? = ( h Tan ? ( ? ) - D ? ? 2 Cos ? ( ? ) ) 2 + h 2 , and, using said distance ? to obtain a point of location of the aircraft in an offset runway reference frame.
    Type: Grant
    Filed: June 4, 2010
    Date of Patent: March 25, 2014
    Assignee: Thales
    Inventor: Thierry Boulay
  • Patent number: 8660722
    Abstract: A target vertical speed, to be applied to the aircraft upon the initiation of the aircraft's flaring phase, is defined in relation to the ground. An optimized ground slope associated with an approach path to be tracked during the landing, is then determined as a function of the determined target vertical speed and of at least one outside parameter. This optimized ground slope is at least equal to a predefined ground slope. Upon interception by the aircraft with the approach path, the aircraft is guided to track the determined optimized ground slope associated with the approach path and reach the target vertical speed upon initiation of the flaring phase.
    Type: Grant
    Filed: March 6, 2012
    Date of Patent: February 25, 2014
    Assignees: Airbus (SAS), Airbus Operations (SAS)
    Inventors: Anne Dumoulin, Martin Scheuermann
  • Patent number: 8630754
    Abstract: The present invention relates to a method for replacing legs in an air navigation procedure described as a series of legs, the legs forming part of an initial family of legs. The method includes: a step of determining a restricted family of legs included in the initial family of legs, so that each leg not belonging to the restricted family corresponds to a combination of legs belonging to the restricted family: The method also includes: a step of replacing in the navigation procedure the legs not belonging to the restricted family with combinations of legs belonging to the restricted family.
    Type: Grant
    Filed: December 5, 2007
    Date of Patent: January 14, 2014
    Assignee: Thales
    Inventors: François Coulmeau, François Hoofd
  • Patent number: 8630805
    Abstract: A method of mapping a space using a combination of radar scanning and optical imaging. The method includes steps of providing a measurement vehicle having a radar system and an image acquisition system attached thereto; aligning a field of view of the radar system with a field of view of the image acquisition system; obtaining at least one radar scan of a space using the radar scanning system; obtaining at least one image of the space using the image acquisition system; and combining the at least one radar scan with the at least one image to construct a map of the space.
    Type: Grant
    Filed: October 20, 2011
    Date of Patent: January 14, 2014
    Assignee: Robert Bosch GmbH
    Inventors: Jan Becker, Oliver Schwindt
  • Patent number: 8630756
    Abstract: An onboard monitor that ensures the accuracy of data representing the calculated position of an airplane during final approach to a runway. This airplane position assurance monitor is a software function that uses dissimilar sources of airplane position and runway data to ensure the accuracy of the respective data from those dissimilar sources. ILS data and GPS or GPS/Baro data are the dissimilar sources of airplane position data used by this function. This function will calculate the airplane's angular deviations from the runway centerline and from the glide slope with onboard equipment and then compares those angular deviations to the ILS angular deviation information.
    Type: Grant
    Filed: April 12, 2011
    Date of Patent: January 14, 2014
    Assignee: The Boeing Company
    Inventors: Steven L. Fleiger-Holmes, Timothy Allen Murphy, Jean Marie Crane
  • Patent number: 8626364
    Abstract: The invention relates to method characterized in that said method comprises steps of acquiring movements, calculating the mean position, calculating position predictions, and calculating minimum grid (5) movement speeds, and a step of acquiring the position of the drone (4) so that, if the drone cannot follow the movements of the grid and the movements of the grid are small, i.e. smaller than the radius of the latter, it is possible to apply a landing strategy by monitoring the mean position of the grid, and if the movements of the grid are large, i.e. larger than the radius of the grid, it is possible to apply a landing strategy by positioning at the minimum speeds of the grid, and if the drone (4) can follow the movements of the grid (5) and the movements of the grid are small, i.e. smaller than the radius of the grid, it is possible to apply a landing strategy according to the mean position of the grid, and if the movements of the grid are large, i.e.
    Type: Grant
    Filed: October 13, 2009
    Date of Patent: January 7, 2014
    Assignee: DCNS
    Inventor: Julien Pierre Guillaume Moresve
  • Publication number: 20130321201
    Abstract: Systems and methods for the selection of antennas in aircraft navigation systems are provided. In one embodiment, a navigation receiver system for an aircraft comprises: a first aircraft antenna that receives transmitter signals from fixed-location ground transmitters and a second aircraft antenna that receives transmitter signals from the fixed-location ground transmitters, wherein the first aircraft antenna has a first gain pattern that is different from a second gain pattern of the second aircraft antenna; a switch coupled to a first receiver and the first and second aircraft antenna; and a switch controller coupled to the switch. The switch controller operates the switch to electrically couple the first receiver to either the first or second aircraft antenna based on a determination of whether the first gain pattern or the second gain pattern provides higher gain in a direction of a first fixed-location ground transmitter of the fixed-location ground transmitters.
    Type: Application
    Filed: June 1, 2012
    Publication date: December 5, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: John Savoy, Sidney Richard Strong, Alfonso Malaga, Anthony H. Luk
  • Patent number: 8601401
    Abstract: An apparatus for synchronizing cursor events may include a processor. The processor may be configured to receive an indication of a cursor event of a cursor presented within and associated with a sourcing window of a user interface that also includes a sourced window, wherein the cursor of the sourcing window indicates a geographical location within the geographical area presented by the sourcing window. Additionally, the processor may be configured to communicate information reflecting the cursor event to the sourced window. The processor may further be configured to subject the cursor of the sourced window to the cursor event reflected by the information to thereby synchronize a cursor event of the cursor of the sourced window with the cursor event of the cursor of the sourcing window, wherein the cursor of the sourced window indicates the geographical location indicated by the cursor of the sourcing window.
    Type: Grant
    Filed: January 30, 2009
    Date of Patent: December 3, 2013
    Assignee: Navico Holding AS
    Inventors: Aaron Coleman, Lance Lybarger, Kevin Brown
  • Patent number: 8600589
    Abstract: A processor calculates a safe landing zone for an aircraft. The processor executes the following steps: (a) converting 4D point cloud data into Cartesian coordinates to form a height map of a region; (b) segmenting the height map to form boundaries of an object in the region; and (c) determining maximum height within the boundaries of the object. Also included are (d) determining if the maximum height is greater than a predetermined height to form a vertical obstruction (VO) in the region; and (e) determining if the VO is in the line of sight (LOS) of the aircraft to classify the landing zone as safe or unsafe. The processor further includes the step of: (f) forming a slope map over the height map.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: December 3, 2013
    Assignee: Exelis, Inc.
    Inventors: Javier Mendez-Rodriguez, Christopher T. Rodgers
  • Patent number: 8584989
    Abstract: The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels.
    Type: Grant
    Filed: September 20, 2011
    Date of Patent: November 19, 2013
    Assignee: Messier-Bugatti-Dowty
    Inventors: David Lemay, David Frank, Michel Basset, Yann Chamaillard
  • Patent number: 8532849
    Abstract: A present novel and non-trivial system, device, and method for presenting course deviation information on an aircraft display unit are disclosed. Lateral/vertical boundaries are established based upon lateral/vertical navigation data provided by one or more navigation data sources. Lateral/vertical deviation symbology data set(s) representative of lateral/vertical deviation scale(s) are generated and adapted to the lateral/vertical navigation data. The adapted lateral/vertical deviation symbology data set(s) representative of adapted lateral/vertical deviation scale(s) are provided to a display unit, whereby symbology(ies) of such adapted scale(s) are presented on a screen of the display unit. Each adapted scale is comprised of a desired course indicator and at least one deviation indicator, where the desired course indicator corresponds to a desired course and each deviation indicator corresponds to one navigation boundary.
    Type: Grant
    Filed: September 29, 2010
    Date of Patent: September 10, 2013
    Assignee: Rockwell Collins, Inc.
    Inventor: Hung-i B. Tsai
  • Patent number: 8521343
    Abstract: A system for autonomous direction of an aircraft to emergency/contingency landing sites incorporates a terrain mapping sensor and an onboard processor receiving terrain data from the terrain mapping sensor. The processor employs software modules for processing the terrain data to produce a terrain map and for creating a landing profile based on the terrain map.
    Type: Grant
    Filed: August 2, 2011
    Date of Patent: August 27, 2013
    Assignee: The Boeing Company
    Inventor: Charles B. Spinelli
  • Patent number: 8457814
    Abstract: When a vehicle moves into a radar prohibited area preset for the neighborhood of a facility that suffers adverse effects from radar waves, emission of radar waves is stopped, and a voice guidance such as “Radar monitoring is stopped” is sent to a speaker via a voice output unit. Moreover, during a period in which a vehicle is located in a radar prohibited area, an icon that indicates that a radar is being stopped, a mark that indicates an institution for which the radar prohibited area is set, and the scope of the radar prohibited area are displayed on a map image.
    Type: Grant
    Filed: March 26, 2009
    Date of Patent: June 4, 2013
    Assignee: Alpine Electronics, Inc.
    Inventor: Koyo Hasegawa
  • Publication number: 20130066489
    Abstract: Instrument Landing System (“ILS”) localizer captures have historically been prone to performance degradations based upon erroneous estimates of the localizer deviation and deviation rate. The angular nature of the ILS beam and the relatively narrow trusted linear course guidance sector of the beam are the primary causes of many such issues. It is highly desirable to convert the angular guidance data into a rectilinear form when used by an autopilot and/or flight director systems, the latter of which allows for more consistent stability and performance with respect to distance to runway threshold. Systems and methods disclosed herein are for accurately converting angular localizer data into rectilinear localizer data, thus allowing for improved localizer capture performance and stability.
    Type: Application
    Filed: September 8, 2011
    Publication date: March 14, 2013
    Inventor: Andrew Robert Hooks
  • Publication number: 20130041529
    Abstract: A vision system is provided for confirming continuously updated approach information from a global positioning system or an instrument landing system with that from an inertial navigation system. The approach information from the inertial navigation system is displayed when the global positioning system or the instrument landing system is unavailable or whose approach information is determined to be invalid.
    Type: Application
    Filed: August 11, 2011
    Publication date: February 14, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Gang He, Thea L. Feyereisen, Ivan Sandy Wyatt, Ken Leiphon, David Wright
  • 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
  • Patent number: 8374736
    Abstract: An automatic landing system (ALS) includes an automatic landing module. The automatic landing module receives a radio altitude from a radio altimeter and any other sensor inputs for use by the automatic landing module and generates an ALS elevator command. The ALS also includes a runway slope compensation (RSC) module. The runway slope compensation module receives the ALS elevator command, the radio altitude and an inertial vertical speed from an inertial reference unit and generates an aircraft elevator command and at least one symmetric wing surface command. The aircraft elevator command and the at least one symmetric wing surface command are useable by an aircraft for runway slope compensation.
    Type: Grant
    Filed: December 2, 2009
    Date of Patent: February 12, 2013
    Assignee: The Boeing Company
    Inventor: Brian K. Rupnik
  • Publication number: 20130035810
    Abstract: A system for autonomous direction of an aircraft to emergency/contingency landing sites incorporates a terrain mapping sensor and an onboard processor receiving terrain data from the terrain mapping sensor. The processor employs software modules for processing the terrain data to produce a terrain map and for creating a landing profile based on the terrain map.
    Type: Application
    Filed: August 2, 2011
    Publication date: February 7, 2013
    Applicant: THE BOEING COMPANY
    Inventor: Charles B. Spinelli
  • Patent number: 8346411
    Abstract: An integrated system for providing a reporting point journey log display in an aircraft and for providing the automatic transfer and installation of a reporting point journey log in a ground retention application. The integrated system includes means for procuring and aggregating reporting point on-board aircraft data from aircraft systems. Means are provided for generating a reporting point cockpit message and readback script from the aggregated reporting point onboard aircraft data. The aggregated reporting point onboard aircraft data is automatically transmitted to a receiving ground application for assembling the data into the form of a reporting point journey log. The reporting point journey log is installed into a ground storage application.
    Type: Grant
    Filed: August 16, 2009
    Date of Patent: January 1, 2013
    Assignee: Rockwell Collins, Inc.
    Inventors: Charles B. Dirks, Michael J. Krenz, Kevin Delaney, James L. Scheer, Joseph M. Costello
  • Patent number: 8346412
    Abstract: The inventive flight control assisting device comprises first means (4) for determining the actual aircraft flight conditions, second means (5) for determining, with the aid of said actual flight conditions and a predetermined pattern, a minimum approaching distance corresponding to a minimum distance between projections on the horizontal plane of the aircraft actual position and a touch-down point when said aircraft moves downwards and decelerates according to an optimised approach in such a way that stabilised approaching conditions are attained, and display means (7) for displaying at least said minimum approaching distance on a navigation screen (9) in the form of a first circular arc focused on a position relative to the aircraft which displays the touch-down position.
    Type: Grant
    Filed: May 3, 2006
    Date of Patent: January 1, 2013
    Assignee: Airbus Operations SAS
    Inventors: Isabelle Lacaze, Vincent Foucart, Jean-Louis De Menorval, Didier Zadrozynski, Frédéric Lemoult, Joëlle Barthe, Sébastien Lhote, Irène Hoste Ventos
  • Patent number: 8319667
    Abstract: A system and method of conveying missed approach procedures to a pilot are provided. The system and method include rendering a graphic representation of at least one leg of the missed approach procedure on a display. A determination is made as to whether the aircraft is at least substantially flying the at least one leg of the missed approach procedure. At least one visual characteristic of the rendered graphic is selectively varied based on the determination of whether the aircraft is at least substantially flying the at least one leg of the missed approach procedure.
    Type: Grant
    Filed: March 11, 2008
    Date of Patent: November 27, 2012
    Assignee: Honeywell International Inc.
    Inventors: Roger W. Burgin, Blake Wilson, Sandy Wyatt