Warning Signal Or Alarm Patents (Class 701/9)
  • Patent number: 8478458
    Abstract: A method and a device for activating an automatic piloting mode of an aircraft are disclosed. The device can include means for engaging an automatic pilot mode, when (i) the current distance of the aircraft with respect to a reference position on the ground belongs to a determined distance range, and (ii) the current height of the aircraft is at most equal to a reference height associated to the automatic pilot mode.
    Type: Grant
    Filed: May 21, 2010
    Date of Patent: July 2, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Mathieu Faurie, Jean Muller
  • Patent number: 8473189
    Abstract: The invention relates to a helicopter, comprising a tail jib (12), at least one distance sensor (16.1) attached to the tail jib (12) for capturing a distance (A) from an object (18) that may be present in a surrounding area of the tail jib (12), and an electric evaluation unit (20), which is connected to the distance sensors (16) and equipped to calculate a position of the object (18) relative to the helicopter (10). According to the invention, a collision avoidance apparatus is provided, which is designed to avoid a collision of a person with the tail jib (12).
    Type: Grant
    Filed: August 31, 2009
    Date of Patent: June 25, 2013
    Assignee: Deutsches Zentrum für Luft- und Raumfahrt e.V.
    Inventor: Kessler Christoph
  • Patent number: 8473202
    Abstract: A automation equipment control system comprises a general purpose computer with a general purpose operating system in electronic communication with a real-time computer subsystem. The general purpose computer includes a program execution module to selectively start and stop processing of a program of equipment instructions and to generate a plurality of move commands. The real-time computer subsystem includes a move command data buffer for storing the plurality of move commands, a move module linked to the data buffer for sequentially processing the moves and calculating a required position for a mechanical joint. The real-time computer subsystem also includes a dynamic control algorithm in software communication with the move module to repeatedly calculate a required actuator activation signal from a joint position feedback signal.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: June 25, 2013
    Assignee: C.H.I. Development Mgmt. Ltd. XXIV, LLC
    Inventor: John R. Lapham
  • 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: 8451144
    Abstract: A flap advisory system provides an advisory to a pilot informing that a speed of the aircraft should be attended to because of a current or desired flap setting. More specifically, the flap advisory system compares a measured airspeed of the aircraft either directly to a flap placard speed or to a marginal speed range set below the flap placard speed for a given flap setting. If the measured airspeed is determined to be excessive then the system provides an advisory indicating the airspeed is too fast. Further, the system may provide an advisory when a movement of a flap handle is detected such that continued movement of the flap handle would place the flaps in a setting that is inappropriate for the measured airspeed.
    Type: Grant
    Filed: February 4, 2009
    Date of Patent: May 28, 2013
    Assignee: Honeywell International Inc.
    Inventors: Yasuo Ishihara, Steve Johnson, Kevin J Conner
  • Patent number: 8447512
    Abstract: A process for generating computer flight plans on the Internet with the elements of: a raw XY&Z database of chart data, a data base containing aircraft data, a software system to create VFR, IFR and Road charts, an Internet web site accessible by a Client computer, a software system which computes flight plans requested by the Client computer, a software system which allows for navigation data and aircraft editing by means of the Internet web site Client computer, and a software system which allows for outputting flight plans by means of the Internet web site Client computer. A alternate embodiment includes wherein said elements include a local area network consisting of a service and number of local Client computers or an Intranet network which is connected by means other than wires such as infrared or radio signals.
    Type: Grant
    Filed: November 10, 2009
    Date of Patent: May 21, 2013
    Inventors: Roger Maria Stenbock, Kyle Braden Everson
  • Patent number: 8447442
    Abstract: A method is provided for assisting in rejoining a vertical descent trajectory that an aircraft is assumed to have to follow, using a flight management system FMS embedded onboard the aircraft, and includes the following steps: calculation of a vertical deviation VDEV, in the vertical plane, between the aircraft and the vertical descent trajectory, and comparison between the vertical deviation VDEV and a predetermined deviation threshold SVDEV; when the vertical deviation VDEV reaches the deviation threshold SVDEV, a step during which the activation of an optimized mode for catching up on the vertical descent trajectory is authorized; if the optimized mode for catching up on the vertical descent trajectory is activated, piloting of the aircraft by the flight management system FMS in optimized catch-up mode, that is to say at minimum thrust with a target rejoining speed in level VCRP and a target rejoining speed in downward trajectory, the target rejoining speed in level VCRP being equal to the maximum L/D rati
    Type: Grant
    Filed: December 2, 2010
    Date of Patent: May 21, 2013
    Assignee: Thales
    Inventors: Jérôme Sacle, Christophe Caillaud, Lionel Verot
  • Patent number: 8447444
    Abstract: The device (1) includes means (2, 3, 4) for observing the overall conditions of the aircraft and for determining whether the lateral behavior thereof is normal.
    Type: Grant
    Filed: May 14, 2010
    Date of Patent: May 21, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Pierre Ezerzere, Stéphane Puig
  • Patent number: 8423207
    Abstract: Systems, computer program products, and methods for displaying navigation performance based flight path deviation information during the final approach segment to a runway and during landing of non-precision flight modes are provided. Improved graphical depictions of navigation performance based flight path deviation information provide pilots and flight crew members with clear, concise displays of the dynamic relationship between ANP and RNP, mode and aspect of flight and related procedures, intersecting flight paths, and current actual flight path deviation from a predefined flight path during the final approach segment to a runway and during landing. For example, an enhanced IAN display may include NPS-type deviation scales to show RNP/ANP relationships and predetermined RNP markers to alert the pilots and flight crew members that the FMC has transitioned from an NPS display for RNAV (LNAV/VNAV) flight procedures to an enhanced IAN display for a non-precision (non-xLS) approach and/or landing.
    Type: Grant
    Filed: August 26, 2011
    Date of Patent: April 16, 2013
    Assignee: The Boeing Company
    Inventors: Robert B. Davis, Daniel J. Boorman, L. Kirk Gagnon, William L. Goodman, Alan R. Jacobsen, William A. Miller, James E. Mitchell, Victor A. Riley, William F. Royce, William D. Tafs
  • Patent number: 8412390
    Abstract: An information presentation device includes: a directional information obtaining element for obtaining directional information based on a signal from an enhancement device for safety or comfort of a passenger of a vehicle; an information presentation controller for generating a driving signal based on the directional information; and a stimulation element including multiple vibrators for generating a traveling wave of vibration in an in-vehicle element. A directionality of the traveling wave corresponds to the directional information. The stimulation element transmits the traveling wave to the passenger so that the passenger perceives the directionality of the traveling wave.
    Type: Grant
    Filed: August 5, 2010
    Date of Patent: April 2, 2013
    Assignees: DENSO CORPORATION, Nippon Soken, Inc.
    Inventors: Norio Sanma, Keiji Shigeoka, Sei Iguchi
  • Patent number: 8412388
    Abstract: An assisted piloting method for an aircraft having at least two engines (2, 3) includes monitoring a set of parameters (Ng, T4, Tq) of the engines. A first limit indicator (10) displays information relating to a value of a limiting parameter of the engines. The limiting parameter is the parameter (Ng, T4, Tq) of the engines that is the closest to its limit. An assisted piloting mode is activated during which each parameter (Ng, T4, Tq) is maintained below a predetermined threshold whenever the first limit indicator is not in a position to display the information.
    Type: Grant
    Filed: September 16, 2010
    Date of Patent: April 2, 2013
    Assignee: Eurocopter
    Inventors: Daniel Chaniot, Olivier Voinchet, Francois-Xavier Gaulmin
  • Patent number: 8401860
    Abstract: A voice-activated command and control system for remotely-controlled vehicles includes a voice-activated control module, a microphone, and a verbal or visual feedback indicator such as a speaker. The operator speaks instructions into the microphone to activate control functions on the vehicle. Confirmation of receipt and/or status of the verbally commanded instructions are sent back to the operator such as spoken through the speaker. The microphone and speaker can be implemented, for example, either in a headset (with a microphone and earphones) worn by the operator, or in the hand-held controller for the vehicle. The system can be alternately implemented without the speaker or other feedback element.
    Type: Grant
    Filed: May 6, 2005
    Date of Patent: March 19, 2013
    Inventor: Paul R Evans
  • 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: 8392475
    Abstract: The present invention relates to a method of flying safely and at low altitude in an aircraft, in which method unsafe relief (R0) of terrain is determined as is the position of at least one high point (4, 5) representing an obstacle (4?, 5?) overlying said unsafe relief (R0). A main volume (V0) is added to said unsafe relief (R0), the main volume being defined between a main volume base (2) placed on the unsafe relief (R0) and an envelope (1), thereby obtaining safe relief (R1) for overflying that contains at least said unsafe relief (R0) and said main volume (V0), said main volume base (2) having an area (2?) defined by a closed peripheral curve (3) resting on said unsafe relief (R0), said envelope (1) being generated using a moving segment (S) of predetermined length (L) extending from said high point (4, 5) to a second point (3?) moving along said peripheral curve (3).
    Type: Grant
    Filed: March 9, 2011
    Date of Patent: March 5, 2013
    Assignee: Eurocopter
    Inventors: Richard Pire, Francois-Xavier Filias
  • Patent number: 8376284
    Abstract: Systems and methods for tracing aircraft vortices. One method includes directing a tracer from a first aircraft into a vortical flow generated by the first aircraft. The method can further include detecting a characteristic corresponding to the presence of the tracer directed into the vortical flow. Based at least in part on the detected characteristic, the method can include directing the flight of the first aircraft, or a second aircraft following the first aircraft, or both.
    Type: Grant
    Filed: November 24, 2009
    Date of Patent: February 19, 2013
    Assignee: The Boeing Company
    Inventors: Michael S. Lewis, Jere S. Meserole, Michael J. Dunn, Brian J. Tillotson
  • Patent number: 8380369
    Abstract: The device for checking speed intended for an aircraft ready to land on deck on a moving vehicle, the aircraft having a current vertical speed, called the first speed, and a threshold value of vertical downward speed relating to the vertical speed of the moving vehicle, called the “low threshold”, the ship having an absolute vertical speed, called the second speed, comprises a display and means for receiving data originating from the aircraft, notably its vertical absolute speed. The device includes a calculator making it possible to generate on the display a graduated speed gauge including a fixed cursor indicating the first vertical speed and a second moving cursor indicating the speed of the ship, a third moving cursor indicating the low threshold, the graduation being centered around the value of the first vertical speed.
    Type: Grant
    Filed: October 28, 2010
    Date of Patent: February 19, 2013
    Assignee: Thales
    Inventors: Rémi Geoffroy, Yannick Thiry, Patrick Cazaux
  • Patent number: 8359130
    Abstract: Disclosed are a method and device for attenuating vertical turbulence encountered by an aircraft during flight. Incorporated into the method and device is a wind determination device, which is used to determine a vertical wind component existing outside the aircraft. A severity level determination unit is used to determine a severity level of the vertical wind component determined by the wind determination device. A control unit calculates at least one control order based on the vertical wind component determined by the wind determination device. In addition, the control unit determines the actual existence of activation conditions determined according to the severity level determined by the severity level determination unit. Upon verifying the activation conditions, the control unit transmits the control order to at least one actuator of the at least one controllable movable member.
    Type: Grant
    Filed: October 9, 2006
    Date of Patent: January 22, 2013
    Assignee: Airbus Operations SAS
    Inventors: Alexandre Colomer, Xavier Dal Santo
  • Patent number: 8340842
    Abstract: The present invention provides methods and apparatuses that reduce pilot workload and increase the performance and efficiency of the pilot's control of the aircraft. The present invention comprises methods and apparatuses for determining the presence and type of an emergency condition, for example by detecting corresponding sensor outputs or by accepting input from a pilot or a combination thereof; and then responding to that emergency by initiating a pre-determined set of actions specific to the determined emergency. Embodiments of the invention can include the ability to monitor engine conditions as well as control electrical functions such as the fuel boost pump, alternator field, battery contactor and other important electrical devices. Some examples described below assume a single-engine piston aircraft for ease of illustration. The invention can also be applied to multi engine and turbine powered aircraft as well.
    Type: Grant
    Filed: October 19, 2007
    Date of Patent: December 25, 2012
    Assignee: Vertical Power, Inc.
    Inventors: Marc Ausman, Kevin DeVries
  • Patent number: 8339285
    Abstract: A method of alerting an occupant of a seat assembly of the occurrence of a triggering event comprising the steps of monitoring for the occurrence of the triggering event, vibrating the seat assembly and/or probing the seat assembly.
    Type: Grant
    Filed: July 27, 2009
    Date of Patent: December 25, 2012
    Assignee: The Boeing Company
    Inventors: Kelly L. Boren, Dianne L. McMullin, Rush F. Green, Jr., Frank P. Santoni
  • Patent number: 8340906
    Abstract: A method and apparatus for searching and generating trajectory content in a navigation device are provided. The method includes establishing a predetermined search region from a current position; extracting information about first parcels included in the established search region and information about second parcels including information about links of specific trajectory content; and determining whether the specific trajectory content is included in the established search region by comparing the information about the first parcels with the information about the second parcels.
    Type: Grant
    Filed: June 8, 2009
    Date of Patent: December 25, 2012
    Assignee: Samsung Electronics Co., Ltd.
    Inventors: Min-chul Jung, Jeong-hoon Park
  • Patent number: 8335638
    Abstract: A system according to aspects of the present invention includes a processor, a user interface (including a display) in communication with the processor, and a memory in communication with the processor. The processor executes instructions stored in the memory to present a first symbol on the display of the user interface that indicates the bearing to an off-scale vehicle, and to present a second symbol on the display that indicates the path of travel of the off-scale vehicle. The present invention provides a more accurate representation of the bearing and track of off-scale traffic compared to conventional traffic display systems.
    Type: Grant
    Filed: February 22, 2010
    Date of Patent: December 18, 2012
    Assignee: Aviation Communication & Surveillance Systems LLC
    Inventors: Richard D. Ridenour, Peter Bobrowitz
  • Patent number: 8306679
    Abstract: The present invention relates to a method of protecting an aircraft in approach by signalling against the risks of collision with the terrain in steep-sided environments, in order to avoid unwanted warnings emanating from the clearance sensors of the onboard TAWS system while protecting the aircraft when it fails to observe the published procedure, and this equally in a landing procedure and in a take-off procedure. The method includes conferring an additional function on the conventional TAWS functions, specific to the detection of the potential risks of collision of the aircraft with the terrain when following procedures of reduced protection corridor type, and this without modifying either the logics or the characteristics of the clearance sensor or sensors as currently defined in the TAWSs of the state of the art.
    Type: Grant
    Filed: November 13, 2008
    Date of Patent: November 6, 2012
    Assignee: Thales
    Inventors: Hugues Meunier, Nicolas Marty, Aurélie Sallier
  • Patent number: 8306677
    Abstract: The invention relates to a method for automatic detection of turbulence by a second aircraft, by information exchange between the second aircraft and at least a first aircraft. The first aircraft has means for transmitting information and the second aircraft has means for receiving the information transmitted by the first aircraft. The method includes the identification of information about turbulence liable to be encountered by the second aircraft, by analyzing the information received from the first aircraft. An alarm is activated on the basis of the turbulence information.
    Type: Grant
    Filed: November 19, 2007
    Date of Patent: November 6, 2012
    Inventors: Guy Deker, Jérôme Sacle, François Coulmeau
  • Patent number: 8306678
    Abstract: The present invention relates to a device and methods for filtering anti-collision alerts for aircraft having a locating system charting the position of the aircraft and estimating the precision of its position. A navigation system of the aircraft calculates at least the actual speed of the aircraft, the speed instruction and a first deviation between the instruction and the actual speed, and the deviation being compared with a first reference overshoot threshold. An anti-collision system generates alerts. An alarms manager of the aircraft centralizes the alerts transmitted by the terrain anti-collision equipment of the aircraft to the crew. The alerts each posses a coding of the danger level, and the danger levels form part of a first predetermined set. The alert filter according to the invention filters sets of alerts according to the coding of their danger level.
    Type: Grant
    Filed: March 13, 2008
    Date of Patent: November 6, 2012
    Assignee: Thales
    Inventors: Stéphane Fleury, Nicolas Marty, Julia Percier
  • Patent number: 8301319
    Abstract: There is provided a personal navigation system, including a head-mounted orientation sensor, a coordinate position sensor, a head-mounted display, and a processor receiving an input from the head-mounted orientation sensor and an input from the coordinate position sensor and providing a visually sensible output for displaying on the head-mounted display.
    Type: Grant
    Filed: February 14, 2012
    Date of Patent: October 30, 2012
    Assignee: Lumus Ltd.
    Inventors: Zvi Lapidot, Abraham Aharoni
  • Patent number: 8295996
    Abstract: The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax).
    Type: Grant
    Filed: September 21, 2009
    Date of Patent: October 23, 2012
    Assignee: Airbus Operations SAS
    Inventors: Paule Botargues, Xavier Dal Santo, Pierre Fabre, Xavier Guery
  • Patent number: 8290641
    Abstract: Aircraft attitude systems are provided. A representative aircraft attitude system includes: a detection system operative to determine an attitude of an aircraft in which the detection system is mounted; a warning system operative to alert a pilot when the attitude of the aircraft corresponds to at least one predefined attitude parameter from a set of predefined attitude parameters, the predefined attitude parameters including pitch, bank and yaw; and a recovery system operative to provide progressive flight control positioning directives to the pilot for returning the aircraft to a flight attitude within the predefined attitude parameters.
    Type: Grant
    Filed: April 13, 2010
    Date of Patent: October 16, 2012
    Assignee: Pilot Disorientation Prevention Technologies, L.L.C.
    Inventors: Jerry Lee Marstall, Shakeel Mozaffar
  • Patent number: 8280622
    Abstract: A system indicating to a pilot that an aircraft has passed the limit-point of success of a standard vertical avoidance maneuver is disclosed. To determine the limit-point, the system monitors a penetration of a model of the terrain being flown over into a first protection volume linked to the aircraft and configured so as to model a standard vertical avoidance maneuver path executed without delay. To determine disengagement azimuth sectors, the system monitors the penetrations of the model of the terrain being flown over into a second protection volume with large azimuth aperture, linked to the aircraft and configured so as to contain the limit-point protection volume and, for the various azimuths covered, paths of a composite maneuver beginning with change-of-heading maneuvers with which to reach the azimuth concerned and continuing with the standard terrain vertical avoidance maneuver.
    Type: Grant
    Filed: October 31, 2006
    Date of Patent: October 2, 2012
    Assignee: Thales
    Inventors: Hugues Meunier, Nicolas Marty
  • Patent number: 8275495
    Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.
    Type: Grant
    Filed: October 7, 2009
    Date of Patent: September 25, 2012
    Assignees: Airbus Operations SAS, Airbus
    Inventors: Fabien Joyeux, Adrien Ott, Melanie Morel, Romain Merat, Stephane Dattler, Francois Barre, Armelle Seillier
  • Patent number: 8255174
    Abstract: A method and device for determining critical buffeting loads on a structure of an aircraft is disclosed. The device (1) comprises means (2, UC) implementing a semi-empirical method for determining the critical loads generated by some buffeting on the structure of the airplane.
    Type: Grant
    Filed: May 27, 2010
    Date of Patent: August 28, 2012
    Assignee: Airbus Operations (SAS)
    Inventors: Guillermo Jenaro Rabadan, Juliane Havas, Stéphane Soumillon, Carole Despre-Flachard
  • Patent number: 8249762
    Abstract: The invention relates to a device for monitoring obstructions for an aircraft including data storage, an anticollision device and viewing devices, wherein the monitoring device comprises a detector to detect in real-time obstructions, of terrain type and of human constructions type, in a close environment of the aircraft in a flight situation, a sensor to identify the obstructions at risk calculating identification parameters, a circuit to calculate criticality of the obstructions, a display to display both the obstructions with the identification and criticality parameters of the obstructions, and a generator of alerts to describe the situation according to a combination of the identification and criticality parameters. One or more embodiments of the invention is a monitoring system adapted for zones close to the aircraft and in the flight zones not visible to the crew. One or more embodiments of the invention applies particularly to helicopters executing low-altitude flights.
    Type: Grant
    Filed: June 4, 2009
    Date of Patent: August 21, 2012
    Assignee: Thales
    Inventors: Laurent Flotte, Nicholas Marty, Pascal Gayraud
  • Patent number: 8249799
    Abstract: The invention relates to a method of presenting zones at risk for an aircraft comprising a system of databases, a processor, an anticollision device and a viewing device, wherein to display on the viewing device the zones at risk in relation to the obstacles, the processor carries out the steps of: acquiring obstacle data, the data corresponding to obstacles situated in the aircraft's close displacement zone; calculating the risk of collision with each of the obstacles of the displacement zone; calculating the limits of the zones at risk of collision in the close displacement zone, these limits representing the positions from which the anticollision device might possibly produce collision alerts in relation to the obstacles if the aircraft were to steer towards the obstacle while maintaining the instantaneous flight parameters; and displaying the limits of zones at risk.
    Type: Grant
    Filed: June 8, 2009
    Date of Patent: August 21, 2012
    Assignee: Thales
    Inventors: Laurent Flotte, Nicolas Marty, Fabien Vittoz
  • Patent number: 8234020
    Abstract: A terrain awareness and warning system (“TAWS”) provides input to a terrain alert (“TA”) processor from at least one real-time aircraft system or sensor and a source of terrain data; the processor determines a terrain clearance surface and a terrain airspace alert surface, and if one surface penetrates the other, the processor generates an alert signal and provides an alert signal to a crew alerting system. The two surfaces are determined by the processor by executing an algorithm(s) embedded in software containing the disclosed embodiments and methods. At least one criterion used to define an aircraft terrain alert surface is programmed to include real-time and/or static input factor data provided by at least one system or sensor input from an aircraft. Such input factor could be used to define a terrain clearance surface.
    Type: Grant
    Filed: February 8, 2008
    Date of Patent: July 31, 2012
    Assignee: Rockwell Collins, Inc.
    Inventors: Joel M. Wichgers, Richard D. Jinkins, Patrick D. McCusker, Richard M. Rademaker
  • Patent number: 8200379
    Abstract: This invention relates to an intelligence system on board an aircraft that detects an emergency, assesses the situation, and then acts on the situation in a pre-determined manner.
    Type: Grant
    Filed: February 10, 2009
    Date of Patent: June 12, 2012
    Inventors: Dario P. Manfredi, Robert La France
  • Patent number: 8200416
    Abstract: Methods and systems for a displaying a moving map display for an aircraft is provided. The method includes determining a route of intended travel of the aircraft on the moving map display, determining a rank of relative importance of a plurality of aeronautical symbols displayed on the moving map display based on the determined route of intended travel, and de-emphasizing at least one navigation symbol with the moving map display based on the at least one navigation symbol determined rank.
    Type: Grant
    Filed: October 10, 2006
    Date of Patent: June 12, 2012
    Assignee: The Boeing Company
    Inventor: Sven D. Aspen
  • Patent number: 8200421
    Abstract: An altitude profile representative of the terrain overflown by an aircraft is established. Thereafter, an altitude limit curve which comprises an intersection with the altitude profile upon the engagement of a terrain avoidance maneuver is determined. As soon as there is no longer any intersection of the limit curve with the altitude profile, the terrain avoidance maneuver is interrupted.
    Type: Grant
    Filed: October 20, 2009
    Date of Patent: June 12, 2012
    Assignee: Airbus Operations SAS
    Inventors: Paule Botargues, Nicolas Caule, Christelle Ledauphin, Jerome Bailly, Isabelle Lacaze, Sylvain Thezelais, Jerome Goyet
  • Patent number: 8193948
    Abstract: A present novel and non-trivial system, module, and method for presenting runway advisory information are disclosed. A runway reference may be established using data received from a source of navigation reference data, where such data could represent runway information, runway awareness zone information, landing awareness zone information, and/or runway threshold line information. Navigation data representative of at least aircraft location and input factor data may be received from a source. Phase of flight may be determined using input factor data, and a runway advisory data set may be generated as a function of phase of flight and the positional relationship between aircraft location and the runway reference. Runway advisory data set may be representative of advisory information comprised of visual runway advisory information, aural runway advisory information, tactile advisory information, or a combination thereof.
    Type: Grant
    Filed: September 30, 2009
    Date of Patent: June 5, 2012
    Assignee: Rockwell Collins, Inc.
    Inventors: Geoffrey A. Shapiro, Alena L. Benson, Matthew J. Carrico, Randy H. Jacobson
  • Patent number: 8190309
    Abstract: Disclosed is a method and device for detecting lateral dissymmetry of an aircraft. A control parameter determination unit is used to determine a current value of a control parameter representative of all roll control surfaces of the aircraft, and a control parameter comparison unit is used to compare the determined current value with a predetermined reference value. A current deflection angle of a lateral stick of the aircraft is also determined, and the determined current deflection angle is compared with a predetermined angle value. A visual alarm signal is output, when the current value of the roll control surfaces of the aircraft is greater than a predetermined reference value and the lateral stick is at a deflection angle that is greater than a predetermined angle value.
    Type: Grant
    Filed: February 14, 2007
    Date of Patent: May 29, 2012
    Assignee: Airbus Operations SAS
    Inventors: Regis Boe, Dominique Chatrenet
  • Patent number: 8190308
    Abstract: A method and device for detecting a risk of collision of an aircraft, having a profile unit having knowledge of the terrain profile, a determination unit for determining effective values of particular flight parameters, a checking unit for verifying whether a flight path determined by the effective values is compatible with the terrain profile, and a transmitting unit for emitting a warning signal in case of incompatibility. The checking unit includes at least one element for calculating a height variation due to an energy transfer and a total slope variation generated by a speed reduction, during an evasive action, an element deter mining an evasive course using the height variation, and an element verifying whether the evasive course determined is compatible with the terrain profile.
    Type: Grant
    Filed: July 25, 2006
    Date of Patent: May 29, 2012
    Assignee: Airbus Operations SAS
    Inventors: Fabien Pitard, Jean-Pierre Demortier, Florence Aubry
  • Patent number: 8188890
    Abstract: A display system for an aircraft includes a processing unit configured to receive data related to an aircraft profile and to supply display commands with symbology based on the aircraft profile; and a display device coupled the processing unit and configured to receive the display commands and operable to render a three-dimensional view with the symbology based on the aircraft profile. The symbology may include slope symbology.
    Type: Grant
    Filed: November 13, 2008
    Date of Patent: May 29, 2012
    Assignee: Honeywell International Inc.
    Inventor: Gang He
  • Patent number: 8175760
    Abstract: A device comprises means for computing the air-craft (A) current position, means for determining at least one maximum permitted deviation (E1) around a set position of the flight path of the flight plan according to accuracy and integrity performances of said current position computation and to the restriction of a flight range authorized in a flight corridor (6A, 6B), and a display system (7) for displaying at least one a distance scale (9) on a viewing screen (8), at least one a fixed symbol (10) displaying the current position and two movable pointers (13, 14) displaying the limits of said maximum permitted deviation (E1).
    Type: Grant
    Filed: June 19, 2006
    Date of Patent: May 8, 2012
    Assignee: Airbus Operations SAS
    Inventors: Patrice Rouquette, Nolween Laveant, Didier Have, Arnaud Le Tellier
  • Patent number: 8160757
    Abstract: The present invention is a method for providing optimum multi-map overlay in a flight deck navigation display of an aircraft. The method includes outputting absolute terrain data to the navigation display for display by the navigation display. The method further includes receiving a threshold elevation input, the threshold elevation input including a threshold elevation. The method further includes receiving relative terrain data. The method further includes, when the aircraft is located below the threshold elevation, overlaying the relative terrain data onto the absolute terrain data based on the received threshold elevation input. Further, the absolute terrain data and the relative terrain data are concurrently displayed by the navigation display, the displayed relative terrain data being overlaid onto the displayed absolute terrain data.
    Type: Grant
    Filed: May 18, 2007
    Date of Patent: April 17, 2012
    Assignee: Rockwell Collins, Inc.
    Inventors: John C. Frank, Craig D. Pettit, James R. McGinnis
  • Patent number: 8140197
    Abstract: There is provided a personal navigation system, including a head-mounted orientation sensor, a coordinate position sensor, a head-mounted display, and a processor receiving an input from the head-mounted orientation sensor and an input from the coordinate position sensor and providing a visually sensible output for displaying on the head-mounted display.
    Type: Grant
    Filed: February 15, 2006
    Date of Patent: March 20, 2012
    Assignee: Lumus Ltd.
    Inventors: Zvi Lapidot, Abraham Aharoni
  • Patent number: 8140264
    Abstract: The field of the invention is that of onboard terrain anticollision systems for aircraft. Collisions with the terrain while the aircraft is fully controlled have been and still remain one of the main causes of air disasters. Several generations of devices for warning of risk of collision with the terrain have been developed for some thirty years now. The most advanced of these systems comprise means of alarm differing according to the maneuver to be performed by the pilot. It is of course vital that the recommended maneuver best guarantee the safety of the aircraft. The device according to the invention proposes a device comprising the calculation of several different safety surfaces or profiles. Their comparisons with the topographic data of the surrounding terrain make it possible to deduce therefrom the best alarm and the best maneuver to be performed to avoid the collision between the aircraft and the ground.
    Type: Grant
    Filed: December 8, 2004
    Date of Patent: March 20, 2012
    Assignee: Thales
    Inventors: Philippe Salmon, Hugues Meunier
  • Patent number: 8135502
    Abstract: A method and device are provided for automatically adjusting an image of an aircraft navigation screen. The device includes a determining unit for automatically determining, if necessary, a new display configuration making it possible to present on a navigation screen a detected dangerous event, and a display unit for automatically effecting a change of display of the navigation screen by applying this new display configuration.
    Type: Grant
    Filed: February 19, 2007
    Date of Patent: March 13, 2012
    Assignee: Airbus Operations SAS
    Inventors: Yannick Deleris, Christophe Maily
  • Patent number: 8132117
    Abstract: A method and system for highlighting a parameter image representative of a flight parameter of an aircraft to a user in a multi-parameter aircraft instrument display, such as a flat panel display. An electronic instrument display is configured to present parameter images, at least one of which includes a first indicator configured to indicate a specific value (e.g., a target value) for a flight parameter and a second indicator configured to indicate an actual flight parameter value that changes according to variations in the flight parameter. A graphics rendering controller is configured to generate the parameter images and to enlarge a portion of the parameter image when the actual flight parameter value is within a predetermined range from the target value.
    Type: Grant
    Filed: July 2, 2010
    Date of Patent: March 6, 2012
    Assignee: Innovative Solutions and Support, Inc.
    Inventor: Geoffrey S.M. Hedrick
  • Patent number: 8121779
    Abstract: There is provided an information processing apparatus capable of communicating with an information management apparatus storing service information including place information, service content information, and start time information; the information processing apparatus including a communication portion; a position measurement portion for generating positional information; a data acquiring portion for acquiring, based on an input search condition, service information satisfying the search condition from the information management apparatus; and a list generating portion for generating a presentation list recorded with information on a service providing place capable of receiving the service at a provision start time based on the positional information, the place information and the start time information of the acquired service information, and time information defining a time the positional information is generated.
    Type: Grant
    Filed: December 9, 2008
    Date of Patent: February 21, 2012
    Assignee: Sony Corporation
    Inventors: Takayasu Kon, Yasunori Kamada, Yoichiro Sako
  • Patent number: 8120615
    Abstract: A method and system for generating a representation of a terrain. The method of generating a representation of a terrain comprises the steps of selecting a set of colors, the colors comprise at least a plurality of colors, determining a minimum terrain elevation, and determining a maximum terrain elevation. A plurality of terrain bands is computed based in part on the set of colors, the minimum terrain elevation, and the maximum terrain elevation. At least one of the limited set of colors is assigned to each of the plurality of the plurality of terrain bands. The representation of the terrain is generated one of the limited set of colors.
    Type: Grant
    Filed: May 9, 2007
    Date of Patent: February 21, 2012
    Assignee: Honeywell International Inc.
    Inventors: Aaron Gannon, Jeffrey M. Rye
  • Patent number: 8121746
    Abstract: The present invention relates to a method and a device for monitoring the minimum flying altitude of an aircraft.
    Type: Grant
    Filed: March 21, 2007
    Date of Patent: February 21, 2012
    Assignee: Thales
    Inventors: Gilles François, Nicolas Marty, Frédéric Thomas
  • 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