I.l.s. Or Radar Guidance Patents (Class 701/17)
  • 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
  • Publication number: 20120265377
    Abstract: 1—Method for determining the distance of an aircraft from an offset runway (15) during a landing by offset approach, the offset runway (15) being situated at a distance D from a main runway (11) equipped with at least one elevation beacon (12), characterized in that it comprises at least the following steps: determining the height h at which the aircraft (1) is situated, height determined with respect to a point T1 of the offset runway (15), 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 (12) provided by an elevation beacon (12) with which said main runway is equipped (11), 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 , using said distance ? to obtain a point of location of the aircraft in an offset runway reference frame (1
    Type: Application
    Filed: June 4, 2010
    Publication date: October 18, 2012
    Applicant: THALES
    Inventor: Thierry Boulay
  • Patent number: 8290644
    Abstract: In a method for aiding aircraft landing using a GPS and an MLS within the context of a computed axial approach, the method uses coordinates of an azimuth antenna and/or of an elevation antenna as a reference point for the computation of a position of the aircraft in a reference frame centered on the landing runway. This position of the aircraft is thereafter used to determine an angle of azimuth between a longitudinal axis of the landing runway and the aircraft.
    Type: Grant
    Filed: December 19, 2008
    Date of Patent: October 16, 2012
    Assignee: Thales
    Inventor: Ludovic Bouquet
  • Patent number: 8265808
    Abstract: The invention relates to an automatic aircraft landing guidance system having an electromagnetic detecting and locating device, positioned on the ground and a first multifunction transmitting/receiving radiofrequency beacon, on board each guided aircraft and transmitting in particular a continuous wave. The detecting and locating device uses the continuous wave transmitted by the beacon to perform a passive locating intended to improve the accuracy of the measurement of the angular position of the aircraft. It also comprises means for generating and periodically transmitting to the aircraft, via the beacon, information enabling said aircraft to rejoin an optimum landing path from its position. The invention applies more particularly to the guidance of autonomous and automatic aircraft such as drones in the approach and landing phase.
    Type: Grant
    Filed: December 1, 2006
    Date of Patent: September 11, 2012
    Assignee: Thales
    Inventors: Patrick Garrec, Pascal Cornic
  • Patent number: 8239077
    Abstract: A method and a device for an aircraft for detecting noise in a signal of LOC type. A first step includes estimating a first lateral speed of the aircraft according to a first set of parameters. Concurrently, at least one second lateral speed of the aircraft is estimated according to at least one second set of parameters, among which at least one parameter is of different nature from each parameter of the first set of parameters. A second step includes comparing the first lateral speed and the at least one second lateral speed according to a threshold. If the difference between the first lateral speed and the at least one second lateral speed is greater than the threshold, the presence of noise in the signal of LOC type is detected.
    Type: Grant
    Filed: April 25, 2008
    Date of Patent: August 7, 2012
    Assignee: Airbus Operations SAS
    Inventor: Alexandre Colomer
  • Patent number: 8209072
    Abstract: A method and device to assist in the piloting of an aircraft in a landing phase may apply a maximum braking of the aircraft if there is a risk of longitudinal departure from a runway.
    Type: Grant
    Filed: March 19, 2008
    Date of Patent: June 26, 2012
    Assignees: Airbus Operations SAS, Airbus
    Inventors: Fabrice Villaume, Armand Jacob, Robert Lignee
  • Patent number: 8184020
    Abstract: A method displaying a pathway (226, 502) for an aircraft includes receiving (302, 402, 602) an instrument generated course generally in alignment with a runway centerline (214), determining (304, 404, 604) the pathway (226, 502) based on aircraft flight parameters in which the aircraft may fly in order to intersect the instrument generated course, rendering (306, 406, 606) on a display the instrument generated course and the pathway; and periodically repeating (308, 408, 608) the determining and rendering steps. The energy state of the aircraft may be considered in determining the pathway and optional indices (508) may be displayed indicating deviation from the pathway centerline.
    Type: Grant
    Filed: July 29, 2009
    Date of Patent: May 22, 2012
    Assignee: Honeywell International Inc.
    Inventor: Gang He
  • Patent number: 8155807
    Abstract: A method of predicting a target type in a set of target types from at least one image is provided. At least one image is obtained. A first and second set of confidence values and associated azimuth angles are determined for each target type in the set of target types from the at least one image. The first and second set of confidence values are fused for each of the azimuth angles to produce a fused curve for each target type in the set of target types. When multiple images are obtained, first and second set of possible detections are compiled corresponding to regions of interest in the multiple images. The possible detections are associated by regions of interest. The fused curves are produced for every region of interest. In the embodiments, the target type is predicted from the set of target types based on criteria concerning the fused curve.
    Type: Grant
    Filed: March 4, 2009
    Date of Patent: April 10, 2012
    Assignee: Raytheon Company
    Inventors: David M. Doria, Robert T. Frankot
  • Publication number: 20120065817
    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: Application
    Filed: September 23, 2011
    Publication date: March 15, 2012
    Applicant: GULFSTREAM AEROSPACE CORPORATION
    Inventors: Robert S. Takacs, Gary M. Freeman, Glenn L. Connor
  • Patent number: 8116923
    Abstract: Systems and methods for suppressing an unstable alert when the aircraft is in the process of landing on a temporarily displaced threshold. In an example process, a processor on the aircraft determines the aircraft is on an approach to landing on a runway based on information received from one or more data sources on the aircraft, then retrieves predefined glideslope information for the runway from a memory device that is in signal communication with the processor. Next, the processor determines whether position of the aircraft is above the predefined glideslope by a first threshold amount. If the aircraft is determined to be above the predefined glideslope by the first threshold amount, the processor issues an unstable alert only if a flight path angle of the aircraft is greater than an angle of the predefined glideslope by a second threshold amount.
    Type: Grant
    Filed: November 19, 2009
    Date of Patent: February 14, 2012
    Assignee: Honeywell International
    Inventors: Yasuo Ishihara, Steve Johnson
  • Patent number: 8112176
    Abstract: A system of self-organizing mobile robotic agents (MRAs) in a multi-robotic system (MRS) is disclosed. The MRAs use simulations to organize the behaviors of groups of robots in the MRS. The MRAs use software agents to model the MRS and the environment. By developing simulations of environmental change, the system provides methods for the MRS to interact with its environment to produce collective epigenetic behaviors.
    Type: Grant
    Filed: January 30, 2008
    Date of Patent: February 7, 2012
    Inventor: Neal Solomon
  • Patent number: 8082070
    Abstract: Methods and systems for displaying assistance messages to aircraft operators are disclosed. A method in accordance with one embodiment includes receiving an input from an aircraft operator at an aircraft flight deck, comparing a characteristic of the input to at least one target value for the characteristic, and, if the characteristic of the input differs from the at least one target value for the characteristic by at least a threshold amount, displaying an assistance message to the aircraft operator. The assistance message can include a complying input and/or an instruction for creating a complying input. The input and the assistance message can be displayed simultaneously.
    Type: Grant
    Filed: June 25, 2010
    Date of Patent: December 20, 2011
    Assignee: The Boeing Company
    Inventors: Peter D. Gunn, John C. Griffin, III
  • Publication number: 20110231038
    Abstract: A method for confirming mobile base station integrity in a relative GNSS aircraft landing system, the method comprising: determining a relative position of a first GNSS antenna fixed to the mobile base station with respect to a second GNSS antenna also fixed to the mobile base station by processing signals from a GNSS satellite constellation; calculating a distance between the first GNSS antenna and the second GNSS antenna using the measured relative position; comparing a calculated distance to a known fixed distance; and confirming mobile base station integrity if the calculated distance is within a predetermined threshold of the known fixed distance.
    Type: Application
    Filed: March 17, 2010
    Publication date: September 22, 2011
    Applicant: CMC ELECTRONICS INC.
    Inventors: John STUDENNY, Daniel Domey
  • Patent number: 8019490
    Abstract: An imaging and display system provides helicopter pilots with an unobstructed display of a landing area in a brownout or whiteout condition by capturing a high resolution image of the landing area prior to obscuration. Using inertial navigation information from the aircraft or an independent system, the system transforms the image to a desired viewpoint and overlays a representation of the helicopter's current position relative to the landing area. The system thus greatly improves orientation and situational awareness, permitting safe and effective operation under zero visibility brownout conditions.
    Type: Grant
    Filed: September 17, 2007
    Date of Patent: September 13, 2011
    Assignee: Applied Minds, LLC
    Inventors: Bran Ferren, W. Daniel Hillis, Michael Harvey Peterson
  • Publication number: 20110160941
    Abstract: A multifunction airborne radar device includes a plurality of transmit antenna modules and/or receive antenna modules that are fixed relative to the aircraft, placed substantially over the surface of the aircraft so as to form transmit and receive beams, enabling targets to be detected for implementing a sense-and-avoid function. The airborne radar device may also comprise processing means for tracking the detected targets and for generating information sent to an air traffic control centre and/or to a control device on board the aircraft. The processing device may also receive data relating to the aircraft, enabling the antenna beams to be adjusted and the tracking calculations to be refined.
    Type: Application
    Filed: August 31, 2010
    Publication date: June 30, 2011
    Applicant: THALES
    Inventors: Patrick Garrec, Pascal Cornic, Stéphane Kemkemian
  • Patent number: 7970503
    Abstract: A method, apparatus, and computer program product for detecting anomalies in a landing system. In one embodiment, a magnitude difference between a blended inertial deviation magnitude and a raw deviation magnitude is identified to form a magnitude difference. The magnitude difference is compared to a magnitude threshold. If the magnitude difference exceeds the magnitude threshold, an anomaly in the data is detected.
    Type: Grant
    Filed: September 12, 2007
    Date of Patent: June 28, 2011
    Assignee: The Boeing Company
    Inventors: Tiffany R. Lapp, Timothy Allen Murphy
  • Patent number: 7953524
    Abstract: A method of navigating a mobile platform. A reflectable electronic signal is transmitted. A reflection of the reflectable signal is received. A position of the mobile platform is determined based upon the reflection of the reflectable signal. A platform position signal is transmitted to the mobile platform. The platform position signal provides the mobile platform the determined position of the mobile platform. The mobile platform is navigated based upon the platform position signal.
    Type: Grant
    Filed: February 29, 2008
    Date of Patent: May 31, 2011
    Assignee: Rockwell Collins, Inc.
    Inventor: Brian R. Roggendorf
  • Patent number: 7945356
    Abstract: A portable autonomous terminal guidance system can be located in an aircraft landing zone. The terminal guidance system generates a signal indicative of the position, the terrain, and the meteorological conditions where the guidance system is located. A receiving aircraft may process the signal produced by the terminal guidance system to generate a self-contained GPS obstacle-avoidance approach path for the aircraft to the landing zone.
    Type: Grant
    Filed: June 29, 2007
    Date of Patent: May 17, 2011
    Assignee: The BOEING Company
    Inventors: Robert R. Wilkins, Jr., Daniel I. Newman
  • Patent number: 7941251
    Abstract: Systems and methods for performing localizer capture maneuvers are disclosed. In one embodiment, a method includes determining at least one instrument landing system (ILS) threshold of an aircraft, and establishing at least one final approach course (FAC) deviation threshold for the aircraft. The method further includes receiving at least one ILS localizer error, then calculating at least one FAC deviation. The at least one ILS localizer error is compared to the ILS threshold, and the at least one FAC deviation is compared to the FAC threshold. A standard capture maneuver is performed if the at least one ILS localizer error reaches its corresponding ILS threshold prior to the at least one FAC deviation reaching its FAC threshold. However, if the at least one FAC deviation reaches its corresponding FAC threshold prior to the at least one ILS localizer error reaching its corresponding ILS threshold, a modified capture maneuver is performed.
    Type: Grant
    Filed: May 22, 2007
    Date of Patent: May 10, 2011
    Assignee: The Boeing Company
    Inventors: Steven B. Krogh, Andrew R. Hooker
  • Publication number: 20110106345
    Abstract: Examples of the present invention may include a low visibility landing system 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: Application
    Filed: November 3, 2009
    Publication date: May 5, 2011
    Inventors: Robert S. Takacs, Gary M. Freeman
  • Patent number: 7925113
    Abstract: Systems and method of generating compound images having increased sharpness and reduced noise are described. In one aspect, a comparison image signal is determined. The comparison image signal includes pixels with values respectively indexing values of pixels of a first image signal in relation to values of spatially corresponding pixels of a second image signal. The comparison image signal is filtered with a spatial filter. A compound image signal is generated. The compound image signal has pixels with values composed of contributions from the pixel values of the first image signal and the pixel values of the second image signal. The contributions are functions of respective values of spatially corresponding pixels in the filtered comparison image signal in relation to values of noise variation in the filtered comparison image signal.
    Type: Grant
    Filed: April 27, 2007
    Date of Patent: April 12, 2011
    Assignee: Hewlett-Packard Development Company, L.P.
    Inventor: Suk Hwan Lim
  • Patent number: 7917254
    Abstract: Systems and methods for aircraft guidance using a localizer capture criteria for rectilinear displacement data are disclosed. In one embodiment, the method includes determining a rectilinear deviation D between a current aircraft location and a final defined path (FDP) of an aircraft and determining a location at which the aircraft should begin a reposition maneuver based on the rectilinear deviation D. The method starts a reposition maneuver of the aircraft at a location determined based on a relationship between D and characteristics of the aircraft during the reposition maneuver. In some embodiments, the characteristics of the aircraft may include a velocity of the aircraft with respect to ground, an aircraft track angle, a heading of the FDP of the aircraft, a maximum allowed bank angle of the aircraft during a reposition maneuver, and a time allowance for aircraft rollup and rollout.
    Type: Grant
    Filed: August 30, 2007
    Date of Patent: March 29, 2011
    Assignee: The Boeing Company
    Inventor: Steven B. Krogh
  • Patent number: 7907067
    Abstract: A computer-implemented system and method for the processing and presentation of customizable aviation information is disclosed. At plurality of flight information is received over a digital network and is stored in at least a database. The database includes aviation information as well as aviation related content and advertisements. The user is able to customize a series of screen layouts for display using a combination of screen segments containing content stored at least partially in the database. In addition, the user may create personalized messages and status update for display in response to a variety of flight conditions. In one form, the results may be presented using a large display monitor by an aircraft service provider. Additionally, the display may include only flight tracking information relevant to recent and future customers.
    Type: Grant
    Filed: July 15, 2010
    Date of Patent: March 15, 2011
    Assignee: FlightAware, LLC
    Inventors: Daniel Baker, Karl Lehenbauer, David Cameron McNett
  • Patent number: 7908079
    Abstract: Systems, methods and apparatus are provided through which an apparatus located on an airfield provides information to pilots in aircraft on the ground and simultaneously gathers information on the motion and position of the aircraft for controllers.
    Type: Grant
    Filed: September 18, 2006
    Date of Patent: March 15, 2011
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Richard W. Dabney, Susan Vinz Elrod
  • Patent number: 7839322
    Abstract: A method of detecting obstacles on board an aircraft while in the vicinity (44) of a touchdown point (27, 42), includes the following operations: selecting/determining a path (41) to be followed by the aircraft overflying the touchdown point; the aircraft overflying the touchdown point following the overflight path, and during the overflight recording signals/data delivered by an on-board rangefinder observing a portion of space extending below the aircraft; analyzing the rangefinder data to detect the presence of obstacles and to determine their positions in a terrestrial frame of reference, where appropriate to determine their dimensions; and recording the detected obstacle position data, and dimensions, if any, in a memory.
    Type: Grant
    Filed: June 20, 2007
    Date of Patent: November 23, 2010
    Assignee: Eurocopter
    Inventors: François-Xavier Filias, Jean Sequeira
  • Publication number: 20100286852
    Abstract: In a method for aiding aircraft landing using a GPS and an MLS within the context of a computed axial approach, the method uses coordinates of an azimuth antenna and/or of an elevation antenna as a reference point for the computation of a position of the aircraft in a reference frame centered on the landing runway. This position of the aircraft is thereafter used to determine an angle of azimuth between a longitudinal axis of the landing runway and the aircraft.
    Type: Application
    Filed: December 19, 2008
    Publication date: November 11, 2010
    Applicant: THALES
    Inventor: Ludovic Bouquet
  • Patent number: 7831345
    Abstract: A method of driving mine vehicles in a mine, and a transport system. A plurality of mine vehicles is arranged in succession and driven in convoy between working areas. A master vehicle in the convoy is driven manually, and slave vehicles follow the master, provided with no mechanical connection. In the working areas, the convoy is disassembled, since single vehicles are each driven separately. When assigned tasks in the working areas have been completed, the vehicles are reassembled into a convoy so as to be driven to a next working area.
    Type: Grant
    Filed: October 2, 2006
    Date of Patent: November 9, 2010
    Assignee: Sandvik Mining and Construction Oy
    Inventors: Timo Heino, Pekka Vauramo
  • Publication number: 20100256840
    Abstract: A method for radar aided positioning of an air vehicle for approach and landing is described. The method includes integrating global navigation satellite system (GNSS) data and inertial data to calculate a position of the air vehicle, scanning the environment forward of the air vehicle with a radar, and accessing a database of terrain features and their radar signatures. The method further includes matching features in the radar scan data to the radar signatures in the database to determine an actual position of the air vehicle and synthesizing glide slope and localizer signals for the approach and landing based on the determined actual position.
    Type: Application
    Filed: May 22, 2006
    Publication date: October 7, 2010
    Inventors: Curtis J. Call, David E. Hedin, David C. Vacanti
  • Publication number: 20100256841
    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: Application
    Filed: April 2, 2010
    Publication date: October 7, 2010
    Applicant: THALES
    Inventors: Patrick Garrec, Pascal Cornic, Eric Barraux
  • Patent number: 7786900
    Abstract: Navigation of an aircraft is facilitated through the displaying on a map of an over flown region, and of the limits of zones within range of the aircraft in an emergency situation. The points of the zones within range of the aircraft are tagged on the basis of: an estimate of the vertical margins to reach these points, taking into account non-maneuverability zones neighboring the aircraft to be circumvented; a vertical flight profile to be complied with; and a safety height margin.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: August 31, 2010
    Assignee: Thales
    Inventors: Elias Bitar, Nicolas Marty
  • Patent number: 7788034
    Abstract: One popular military aircraft mission is to meet or rendezvous with another aircraft. Presently used systems have limitations in rendezvous distance, low accuracy of computed rendezvous intercept position, and wrong results in special rendezvous scenarios such in polar regions or on a collision path. The present invention makes use of a numerical algorithm to accurately compute the rendezvous interception position with a preselected tolerance/resolution. The algorithm makes no assumption of angles and uses a proven Sodanos equation to compute a distance between two points on the earth or to compute a second position away from a first position at a known distance and bearing. Using the invention, the rendezvous intercept position can be computed with greater accuracy and a further distance in any region of the globe than the prior art methods and can be used even if the aircraft are in a rendezvous or collision/chasing path.
    Type: Grant
    Filed: June 22, 2005
    Date of Patent: August 31, 2010
    Assignee: Honeywell International Inc.
    Inventor: Tien D. Bui
  • Patent number: 7783425
    Abstract: An integrity monitoring method for an aircraft is disclosed. The integrity monitoring method includes determining a set of non-uniform weights. The non-uniform weights are based on a least squares approximation of a linearized measurement equation. The integrity monitoring method also includes applying the non-uniform weights in a receiver autonomous integrity monitoring (RAIM) system. Further, the integrity monitoring method includes determining a reduced integrity limit based on the output of the RAIM system.
    Type: Grant
    Filed: June 29, 2005
    Date of Patent: August 24, 2010
    Assignee: Rockwell Collins, Inc.
    Inventors: Patrick Y. Hwang, R. Grover Brown
  • Patent number: 7774131
    Abstract: The invention relates to a method of automatic navigation assistance for an aircraft. A capture zone being a zone in which the aircraft can capture a predetermined vertical profile segment by applying a transition between the guidance submode which the aircraft is in and the guidance submode adapted to the following of the vertical profile segment to be captured, it comprises the step consisting in determining the width of the capture zone as a function of the height h of the vertical profile to be captured and of the speed v which the aircraft has when plumb with this height when the aircraft is not on the profile or at this height when the aircraft is on the profile.
    Type: Grant
    Filed: September 23, 2003
    Date of Patent: August 10, 2010
    Assignee: Thales
    Inventor: Guy Deker
  • Patent number: 7761196
    Abstract: System, method and computer program product for determining bearing using ADS-B and TCAS standard reply bearing estimates are disclosed. In one embodiment, a method for determining bearing based upon ADS-B signals includes receiving ADS-B signals and standard transponder reply signals. A first bearing estimate is based on the ADS-B signal. A second bearing estimate is based on the standard transponder reply signals. A database is developed according to the first and second bearing estimates via the ADS-B and standard transponder reply signals. In one embodiment, where ADS-B signals are unavailable, associated ADS-B signals associated with the standard transponder reply previously stored in the database are used to determine bearing.
    Type: Grant
    Filed: August 19, 2005
    Date of Patent: July 20, 2010
    Assignee: Honeywell International Inc.
    Inventors: Ruy L. Brandao, Ruy C. Brandao, Sr., Christine M. Haissig, John Weed, Eric A. Euteneuer
  • Patent number: 7706978
    Abstract: A method for estimating unknown parameters (pan angle (?), instantaneous tilt angle (?) and road geometry of an upcoming road segment) for a vehicle object detection system. The vehicle object detection system is preferably a forward looking, radar-cued vision system having a camera, a radar sensor and an processing unit. The method first estimates the pan angle (?), then corrects the coordinates from a radar track so that pan angle (?) can be treated as zero, and finally solves a least squares problem that determines best estimates for instantaneous tilt angle (?) and road geometry. Estimating these parameters enables the vehicle object detection system to identify, interpret and locate objects in a more accurate and efficient manner.
    Type: Grant
    Filed: September 2, 2005
    Date of Patent: April 27, 2010
    Assignee: Delphi Technologies, Inc.
    Inventors: Jan K. Schiffmann, David A. Schwartz
  • Publication number: 20100017053
    Abstract: Systems and methods for performing localizer capture maneuvers are disclosed. In one embodiment, a method includes determining at least one instrument landing system (ILS) threshold of an aircraft, and establishing at least one final approach course (FAC) deviation threshold for the aircraft. The method further includes receiving at least one ILS localizer error, then calculating at least one FAC deviation. The at least one ILS localizer error is compared to the ILS threshold, and the at least one FAC deviation is compared to the FAC threshold. A standard capture maneuver is performed if the at least one ILS localizer error reaches its corresponding ILS threshold prior to the at least one FAC deviation reaching its FAC threshold. However, if the at least one FAC deviation reaches its corresponding FAC threshold prior to the at least one ILS localizer error reaching its corresponding ILS threshold, a modified capture maneuver is performed.
    Type: Application
    Filed: May 22, 2007
    Publication date: January 21, 2010
    Applicant: THE BOEING COMPANY
    Inventors: Steven B. Krogh, Andrew R. Hooker
  • Patent number: 7636620
    Abstract: A distribution device for a glide guidance component, the distribution device including an array of antenna elements installed on a pylon. The distribution device includes: a first and a second input for receiving a CSB (carrier plus sideband) input signal and an SBO (sideband only) input signal respectively, a plurality of outputs connectable to the array and including a first and a second output for the first and second output signals, respectively; each of said output signals including a CSB component and an SBO component. The array of antenna elements is such as to irradiate an image-less type pattern and the distribution device is such that the outputs have an substantially equal amplitude value for each pair arranged symmetrically around a central point of the array and a phase difference which is identical for the two CSB and SBO components.
    Type: Grant
    Filed: December 9, 2004
    Date of Patent: December 22, 2009
    Assignee: Thales Italia S.p.A.
    Inventor: Giuseppe Bertocchi
  • Patent number: 7603207
    Abstract: A control system for remotely controlling a mobile platform includes a ground-based control station and a surrogate processor. The surrogate processor is remotely located from both the mobile platform and the ground-based control station and includes a communication gateway and software. The communication gateway is in communication with the software, the ground-based control station, and the mobile platform and is capable of transmitting information therebetween. The software generates a control message based on commands received from the ground-based control station to adjust an operational characteristic of the mobile platform. Locating the software and the gateway remotely from the mobile platform also enables a less costly and less complex mobile platform to be constructed.
    Type: Grant
    Filed: May 3, 2005
    Date of Patent: October 13, 2009
    Assignee: The Boeing Company
    Inventors: Michael R Abraham, Brian C Gray
  • Patent number: 7546183
    Abstract: An instrument landing system (ILS) provides signals in space receivable by an aircraft in flight to identify, for example, a point in space at which to start an approach along a glide slope path to a touchdown point on a runway. Atmospheric, ground and other conditions may cause transmission anomalies, so that the ILS signals identify a point in space displaced from its intended position. Systems and methods employed in flight use GPS or other positional data to determine the current displacement of such point, as identified by received ILS signals, from its intended position consistent with ILS specifications. In addition to reception and use of ILS and GPS signals, data on geographic runway location and correct ILS signal in space parameters is used for reference purposes in determining signal in space position discrepancies, glide slope path angular discrepancies, or both.
    Type: Grant
    Filed: March 10, 2006
    Date of Patent: June 9, 2009
    Inventor: Frank Marcum
  • Patent number: 7509217
    Abstract: A vehicle detector includes a detecting apparatus and a determining apparatus. If a plurality of detection points detected by the detecting apparatus forms a group of detection points, the determining apparatus sets a determining virtual window encompassing the group of detection points and determines whether the group of detection points is likely to represent the one vehicle based on a state of movement of the group of detection points with respect to the determining virtual window.
    Type: Grant
    Filed: October 11, 2005
    Date of Patent: March 24, 2009
    Assignee: Alpine Electronics, Inc.
    Inventor: Kenjiro Endoh
  • Publication number: 20090055038
    Abstract: The invention relates to an automatic aircraft landing guidance system having an electromagnetic detecting and locating device, positioned on the ground and a first multifunction transmitting/receiving radiofrequency beacon, on board each guided aircraft and transmitting in particular a continuous wave. The detecting and locating device uses the continuous wave transmitted by the beacon to perform a passive locating intended to improve the accuracy of the measurement of the angular position of the aircraft. It also comprises means for generating and periodically transmitting to the aircraft, via the beacon, information enabling said aircraft to rejoin an optimum landing path from its position. The invention applies more particularly to the guidance of autonomous and automatic aircraft such as drones in the approach and landing phase.
    Type: Application
    Filed: December 1, 2006
    Publication date: February 26, 2009
    Applicant: Thales
    Inventors: Patrick Garrec, Pascal Cornic
  • Publication number: 20080294307
    Abstract: Systems and methods for aircraft guidance using a localizer capture criteria for rectilinear displacement data are disclosed. In one embodiment, the method includes determining a rectilinear deviation D between a current aircraft location and a final defined path (FDP) of an aircraft and determining a location at which the aircraft should begin a reposition maneuver based on the rectilinear deviation D. The method starts a reposition maneuver of the aircraft at a location determined based on a relationship between D and characteristics of the aircraft during the reposition maneuver. In some embodiments, the characteristics of the aircraft may include a velocity of the aircraft with respect to ground, an aircraft track angle, a heading of the FDP of the aircraft, a maximum allowed bank angle of the aircraft during a reposition maneuver, and a time allowance for aircraft rollup and rollout.
    Type: Application
    Filed: August 30, 2007
    Publication date: November 27, 2008
    Applicant: The Boeing Company
    Inventor: Steven B. Krogh
  • Patent number: 7444214
    Abstract: An obstacle detection apparatus and method which can detect the state of an obstacle according to a signal generated when the obstacle detection apparatus collides with the obstacle and a change in the posture of the obstacle detection apparatus caused due to the collision with the obstacle. The obstacle detection apparatus includes a main body which can be moved along the surface of the ground, a movement amount determination module which determines whether the amount of movement of the main body is outside a predefined threshold range, a posture determination module which determines the changed posture of the main body with respect to the surface of the ground according to the amount of movement of the main body, and a state determination module which determines the state of an obstacle based on the results of determination of the movement amount determination module or the posture determination module.
    Type: Grant
    Filed: December 7, 2006
    Date of Patent: October 28, 2008
    Assignee: Samsung Electronics Co., Ltd.
    Inventors: Woo-jong Cho, Dong-yoon Kim, Seong-il Cho, Sung-mun Cho
  • Publication number: 20080234882
    Abstract: Method and device to assist in the piloting of an aircraft in a landing phase. The device (1) comprises means (12) for applying a maximum braking of the aircraft if there is a risk of longitudinal departure from a runway, on a landing.
    Type: Application
    Filed: March 19, 2008
    Publication date: September 25, 2008
    Applicants: AIRBUS France, AIRBUS
    Inventors: Fabrice VILLAUME, Armand Jacob, Robert Lignee
  • Patent number: 7417641
    Abstract: A method and apparatus for converting electronic display aeronautical chart data to aeronautical chart data that is tailored for an avionics display is disclosed. The method and apparatus received by a data processing unit, electronic display aeronautical chart data. The color palette of the electronic display aeronautical chart data is then remapped to improve viewability on the avionics quality display. Finally, signals representative of the remapped colors are sent to the avionics quality display.
    Type: Grant
    Filed: October 16, 2002
    Date of Patent: August 26, 2008
    Assignee: Rockwell Collins, Inc.
    Inventors: Sarah Barber, Lyndon L. Dunbar, Deborah Hardin, Kirschen A. Seah
  • Patent number: 7409272
    Abstract: A method of removing undesired signals in an aviation guidance system may include receiving at least one first desired signal having a first frequency of amplitude modulation, receiving at least one second desired signal having a second frequency of amplitude modulation, and receiving at least one undesired signal having any frequency including a frequency that is substantially the same as or a subharmonic of at least one of the first and second desired signals. The first and second frequencies of amplitude modulation are phase synchronous, and the undesired signals are non-synchronous with at least one of the first and second desired signals. The method may also include identifying the undesired signals and removing the undesired signals.
    Type: Grant
    Filed: September 27, 2005
    Date of Patent: August 5, 2008
    Assignee: Honeywell International Inc.
    Inventor: Charles K. Hanneman
  • Publication number: 20080177432
    Abstract: The method in accordance with the invention is a method of providing a 3D emergency descent trajectory for aircraft comprising the steps of searching for at least one possible better trajectory allowing a secure continuation in relation to the relief and/or the surrounding conditions towards a homing point as soon as a situation requiring an unscheduled modification of the current trajectory occurs, wherein this trajectory is updated as a function of the alterations in the surrounding conditions, as a function of the information provided by the onboard sensors and/or outside information received.
    Type: Application
    Filed: October 10, 2007
    Publication date: July 24, 2008
    Applicant: Thales
    Inventors: Guy Deker, Nicolas Marty, Francois Coulmeau
  • Patent number: 7206675
    Abstract: This invention provides an improvement in the present instrument approach procedure used at airports having an ILS localizer without an accompanying UHF glide-slope. The field strength of the localizer, as measured at the airplane, is used as a basis for producing a glide-slope deviation signal. The shape of the resulting path may be adjusted by changing the input/output characteristic of a localizer receiver.
    Type: Grant
    Filed: April 10, 2006
    Date of Patent: April 17, 2007
    Inventor: Chester B. Watts, Jr.
  • Patent number: 6845304
    Abstract: Deriving inertial-aided deviations for autoland systems during GPS signal interruptions involving an inertial reference system and a GPS landing system can include converting position coordinates of an aircraft from the inertial reference system to runway, lateral, and vertical coordinates. After this conversion, the method calibrates runway distance and lateral distance based on the converted position coordinates from the inertial reference system using runway distance and lateral distance from the GPS landing system with a third-order calibration filter when the aircraft is below a first height above terrain and calibrates vertical distance based on the converted position coordinates from the inertial reference system using vertical distance from the GPS landing system with a second-order calibration filter when the aircraft is below the first height above terrain.
    Type: Grant
    Filed: September 17, 2003
    Date of Patent: January 18, 2005
    Assignee: Rockwell Collins
    Inventor: Shih-Yih R. Young