Air Speed Or Velocity Measurement Patents (Class 701/7)
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Patent number: 8788124Abstract: Systems and methods for the calculation of the approach speed during air to air refueling maneuvers. The systems comprise: a) capturing means of a sequence of digital photograms of the approach operation scenario calibrated in order to determine the real distance corresponding to a pixel of a photogram; b) computational means configured for obtaining the coordinates of the relative trajectory of the receiver aircraft with respect of the tanker aircraft, by means of a sequence of photograms of the approach operation obtained by said capturing means and calculating the speed difference between receiver aircraft and tanker aircraft based on the trajectory defined by the coordinates recorded in said process b1). The invention also refers to the methods for calculating the approach speed.Type: GrantFiled: June 4, 2013Date of Patent: July 22, 2014Assignee: EADS Construcciones Aeronauticas S.A.Inventors: Francisca Coll Herrero, Jose Maria Miranda Orte
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Patent number: 8779945Abstract: A flight display for an aircraft includes a virtual ice accretion meter having a liquid water content portion and an ice thickness portion. A method for determining ice accretion includes integrating over a time period a constant K multiplied by a liquid water content (LWC) and true airspeed (TAS).Type: GrantFiled: March 15, 2011Date of Patent: July 15, 2014Assignee: Sikorsky Aircraft CorporationInventor: Robert James Flemming
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Patent number: 8768540Abstract: There is provided an avionics system that provides several avionics functions within a single LRU. In one embodiment, the system comprises a software-configurable RF assembly, one or more processor assemblies that are configured to provide multiple TAWS/TCAS/Mode S/ADS-B/ATC functions, interfaces to allow connections to aircraft electronics and data loaders, and multipurpose antennas. In one embodiment, a common processor architecture allows generic avionics processors to be configured to operate a number of TAWS/TCAS/Mode S/ADS-B/ATC functions without the need for multiple LRUs, and software-defined RF functions allow RF circuitry that interfaces to the processors to handle current and future communication needs.Type: GrantFiled: April 10, 2007Date of Patent: July 1, 2014Assignee: L-3 Communications CorporationInventors: Cyro A. Stone, James R. Troxel, Gregory T. Stayton
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Patent number: 8768556Abstract: An apparatus defines a protection envelope in an aircraft, including a processor and at least one sensor, each sensor being coupled with the processor, the processor executing at least one neural network based algorithm. The at least one sensor monitors flight parameters of the aircraft thereby generating monitored flight parameters. The processor divides the performance envelope of the aircraft into predefined flight regimes, wherein for each predefined flight regime, the processor defines and stores a suitable protection envelope. The processor determines an estimated flight regime of the aircraft using the neural network based algorithm based on the monitored flight parameters. The processor selects a respective suitable protection envelope for the aircraft based on the estimated flight regime.Type: GrantFiled: November 12, 2010Date of Patent: July 1, 2014Assignee: Elbit Systems Ltd.Inventors: Gershon Ben-Arie, Ilana Segall, Asi Dotan
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Patent number: 8761961Abstract: A method for controlling an unmanned aerial vehicle (UAV) using an electronic device obtains movement data of the electronic device detected by an accelerometer of the electronic device, and converts the movement data of the electronic device to control signals. The method further sends the control signals to the UAV, and changes a flight status of the UAV according to the control signals.Type: GrantFiled: October 20, 2010Date of Patent: June 24, 2014Assignee: Hon Hai Precision Industry Co., Ltd.Inventors: Hou-Hsien Lee, Chang-Jung Lee, Chih-Ping Lo
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Patent number: 8744768Abstract: A method and device establishes trajectory planning, predictions and guidance so as to obtain the satisfaction of a time constraint (RTA). This objective is achieved by undertaking a computation of a trajectory up to the point where the flypast time constraint applies, on the basis of a profile of altitude and speeds, and then by computing the profile of speeds and altitudes making it possible, throughout the computed trajectory, to comply with the RTA. The method is also a method for readapting the trajectory and the vertical profile when during a mission, the data outside the aeroplane have caused the time predictions to drift and the constraint is no longer complied with under the initial speeds and trajectory assumptions.Type: GrantFiled: November 29, 2010Date of Patent: June 3, 2014Assignee: ThalesInventors: Manuel Gutierez-Castaneda, Philippe Chaix, Benoît Dacre-Wright
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Patent number: 8742927Abstract: The invention relates to the automatic detection of the presence of non-authorized persons in the vicinity of an apparatus of the aircraft type. To this end, the invention comprises equipping persons with radio transmitters for identifying them as authorized personnel. The aircraft are also fitted, such as at the existing PODs, with a transceiver device of a radio identification system of the RFID type for recognition of the persons wearing the radio transmitters. Only the persons who are not authorized in the vicinity of the aircraft initiate an alarm procedure.Type: GrantFiled: January 29, 2008Date of Patent: June 3, 2014Assignee: Airbus Operations SASInventor: Pujol Olivier
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Patent number: 8744670Abstract: A method for quickly calculating mileage includes the steps: A, receiving report data from a vehicular terminal and updating data center according to the report data; B, receiving an inquiry request which includes a vehicle number, a first time point which is earlier than a second time point and the second time point which are requested to inquire; C, inquiring the data center to acquire a first total mileage value to which the time point that is proximate to the first time point corresponds and a second total mileage value to which the time point that is proximate to the second time point corresponds; D, obtaining a running mileage L from the first time point to the second time point by subtracting the first total mileage value from the second total mileage value. A system for quickly calculating mileage quickly is also proposed.Type: GrantFiled: September 8, 2010Date of Patent: June 3, 2014Assignee: ChinaGps Co., Ltd (Shenzhen)Inventors: Jie Zhu, Jialiang Chu, Decheng Huang, Youwen Zhang
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Patent number: 8744700Abstract: A device comprising a processor that detects an autonomously sensed change in a vehicle's operational state from an initial state characterized by a sensed vehicle speed equal to about 0; to an immediately succeeding vehicle state characterized by sensed vehicle speed being greater than about 0 and, verification from a reverse operating mode sensor that longitudinal vehicle speed is in a reverse direction; and presumptively signals the thusly detected change of vehicle operational state as an instance of reverse operation of the associated vehicle.Type: GrantFiled: April 25, 2012Date of Patent: June 3, 2014Inventors: Darren Beams, Neil Cawse
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Patent number: 8731756Abstract: In a method for monitoring the operation of a vacuum pump in a brake system, the vacuum pump is operated between an activation pressure and a deactivation pressure to generate a vacuum, the evacuation period between the activation pressure and the deactivation pressure being measured and compared with a reference period. An error signal is generated if the evacuation period exceeds the reference period.Type: GrantFiled: October 11, 2010Date of Patent: May 20, 2014Assignee: Robert Bosch GmbHInventors: Hartmut Krueger, Karl Weidinger, Peter Damm
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Publication number: 20140129057Abstract: Local wind fields can be predicted if both the airspeed and the ground speed of the helicopter are known. An aircraft that uses an inertial navigation unit, autopilot and estimator allows a measure of ground speed to be known with good certainty. The embodiments herein extends this system to allow an estimate of the local wind field to be found without actively using an airspeed sensor, but instead combining the measurements of an accelerometer and a drag force model and a model of controlled aerodynamics of the aircraft to estimate the airspeed, which again can be used to estimate the local wind speed.Type: ApplicationFiled: April 2, 2013Publication date: May 8, 2014Applicant: Prox Dynamics ASInventor: Prox Dynamics AS
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Patent number: 8718840Abstract: A device for estimating the angle of attack of an aircraft moving through the air comprises means for receiving a measured incidence presented locally by the air relative to the aircraft and means for determining the angle of attack of the aircraft as a function of the measured incidence and information about the airspeed of the aircraft. The means for determining the angle of attack of the aircraft comprise means for reading the angle of attack of the aircraft from a look-up table having at least the measured incidence and the airspeed information as inputs. Corresponding system and a corresponding method are also proposed.Type: GrantFiled: May 7, 2008Date of Patent: May 6, 2014Assignees: Airbus Operations S.A.S., AirbusInventors: Thomas Spoerry, Bruno Chauveau
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Patent number: 8718839Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a timer. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated.Type: GrantFiled: December 3, 2010Date of Patent: May 6, 2014Assignee: Evolved Aircraft Systems, L.L.C.Inventors: Michael Louis Everett, Louis Jackson Everett, Mario Ruiz, Jr.
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Patent number: 8712607Abstract: A method for velocity profile based approach to point control for an aircraft includes determining a distance from the aircraft to a target point; determining a velocity command based on the distance to the target point and a desired acceleration; and issuing the velocity command. A velocity profile based approach to point control module for an aircraft and a computer program product comprising a computer readable storage medium containing computer code that, when executed by a computer, implements a method for velocity profile based approach to point control are also provided.Type: GrantFiled: November 1, 2010Date of Patent: April 29, 2014Assignee: Sikorsky Aircraft CorporationInventor: Anthony Litwinowicz
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Patent number: 8712603Abstract: The present invention describes a drive system for an aircraft involving one or more nose wheel motors. Data regarding the nose wheel rotation is used to control the ground travel of the aircraft, to predict potential problems, to provide more precise control over the aircraft, and to improve aircraft safety.Type: GrantFiled: August 2, 2005Date of Patent: April 29, 2014Assignee: Borealis Technical LimitedInventors: Isaiah Watas Cox, Robert Lincoln Carman, Jr.
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Patent number: 8706321Abstract: In one embodiment of a method to reduce vertical position errors of an aircraft, a disturbance input acting on the aircraft may be determined. The magnitude of the disturbance may be converted into a delta lift command if the magnitude of the disturbance is outside a criteria. The delta lift command may be post processed. The delta lift command may be converted into symmetric lateral surface position commands for control surfaces. The symmetric lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the symmetric lateral surface position commands.Type: GrantFiled: August 23, 2012Date of Patent: April 22, 2014Assignee: The Boeing CompanyInventors: Brian K. Rupnik, Sean J. Flannigan
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Patent number: 8700234Abstract: A method of an aircraft communicating a current position status, a current movement status, a current intent, and/or an intended future path, position, or intent of the aircraft may include the aircraft generating explicit first ownship information related to the current position status and/or the current movement status, or current intent of the aircraft, and/or a flight management or other aircraft system of the aircraft generating information related to the intended future path, position, or intent of the aircraft. The aircraft may transmit the explicit first ownship information and/or the second information using an automatic dependent surveillance broadcast system transmitter. An airborne and/or ground receiver may receive the transmitted information related to the explicit first ownship information and/or the second information.Type: GrantFiled: May 20, 2008Date of Patent: April 15, 2014Assignee: The Boeing CompanyInventors: Syed Taji Shafaat, Samuel T. Clark
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Patent number: 8694182Abstract: A flight control system includes an Acceleration and Attitude Command/Velocity Hold mode (AACVH) algorithm which blends attitude commands with acceleration commands. This blending determines a trim attitude for a given rotorcraft flight condition.Type: GrantFiled: April 3, 2007Date of Patent: April 8, 2014Assignee: Sikorsky Aircraft CorporationInventor: Igor Cherepinsky
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Patent number: 8688380Abstract: A method and apparatus in a vehicular telemetry system and a remote data analysis system for detecting an event and switching a data acquisition mode. Checking a state of a data acquisition mode. If the state is in a filtered data state and if an indicator value is at or above a threshold value, then switch the data acquisition mode to an unfiltered data state and acquire unfiltered data. If the data acquisition mode is in an unfiltered data state and if the indicator value is below the threshold value, switch the data acquisition mode to a filtered data state and acquire filtered data.Type: GrantFiled: April 23, 2012Date of Patent: April 1, 2014Assignee: GEOTAB Inc.Inventors: Neil Charles Cawse, Darren Marc Lohmann Beams, Antonios Partheniou, Stelian Dumitrascu
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Patent number: 8686879Abstract: A method and module for displaying a munition release envelope.Type: GrantFiled: September 25, 2008Date of Patent: April 1, 2014Assignee: Sikorsky Aircraft CorporationInventors: Richard H. Lammers, Greg Boria
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Patent number: 8682507Abstract: Disclosed are a method and system for improving real-time determination of flight parameters of an aircraft during flight. A selection module selects and delivers measured values of input parameters to an estimation unit, and the estimation unit uses the input parameters to estimate at least two selected flight parameters. The input parameters are received by the estimation unit on the basis of identified flight mechanics equations associated with the selected flight parameters. The estimation unit includes an extended Kalman filter, which is configured to receive the values of the input parameters and to output joint estimations of the selected flight parameters based on the flight mechanics equations, during the flight of the aircraft.Type: GrantFiled: July 31, 2012Date of Patent: March 25, 2014Assignees: Airbus Operations SAS, Onera (Office National d'etudes et de Recherches Aerospatiales)Inventors: Pierre Ezerzere, Cedric Seren, Georges Hardier
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Patent number: 8682505Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector heading across a ground surface. The aircraft includes a control system in data communication with a model, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The model decouples the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion. The lateral control architecture utilizes the lateral equation of motion to control the aircraft in the lateral direction, while the longitudinal control architecture utilizes the longitudinal equation of motion to control the aircraft in the longitudinal direction. The initialization command logic selectively activates the lateral control architecture and the longitudinal control architecture.Type: GrantFiled: December 11, 2012Date of Patent: March 25, 2014Assignee: Textron Innovations Inc.Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill
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Patent number: 8676409Abstract: Even when a rigidity table stored in a RAM at the time of a start of a brake operation does not coincide with an actual rigidity characteristic of an electric caliper which changes according to brake conditions including how often and how long a brake operation is applied, it is possible to reduce a deviation between a pressing force instruction value and a generated pressing force by updating the characteristic of the relation between a pressing force instruction value and rotational position each time an estimated thrust force value is calculated during one brake operation. It is possible to steadily keep followability to a pressing force instruction according to an actual state of the rigidity characteristic of the electric caliper, thereby ensuring generation of an appropriate brake force.Type: GrantFiled: March 23, 2011Date of Patent: March 18, 2014Assignee: Hitachi Automotive Systems, Ltd.Inventors: Hiroki Takeda, Hirotaka Oikawa, Junichi Ikeda, Daisuke Goto
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Patent number: 8676403Abstract: The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring an actual along-track position and an actual vertical position of the aircraft relative to corresponding desired positions on the predetermined flight path. Throttle commands are generated based on deviations of the actual vertical position of the aircraft from the desired vertical position. Elevator commands are generated based on the deviation of the actual along-track position from the desired along-track position and on the deviation of the actual vertical position from the desired vertical position.Type: GrantFiled: April 15, 2010Date of Patent: March 18, 2014Assignee: The Boeing CompanyInventors: David Garrido-Lopez, Ramon Gomez Ledesma
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Patent number: 8660714Abstract: Aircraft system and method are provided for a first aircraft in an airport environment, the airport environment including a second aircraft. The system includes a sensor on the first aircraft configured to determine a temperature profile of engine exhaust from the second aircraft; and a processing unit coupled to the sensor and configured to construct a velocity profile of the engine exhaust from the second aircraft based on the temperature profile and to generate a warning for a pilot of the first aircraft based on the velocity profile.Type: GrantFiled: February 22, 2011Date of Patent: February 25, 2014Assignee: Honeywell International Inc.Inventors: Gang He, Dave Pepitone
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Publication number: 20140052314Abstract: Systems and methods to provide alerts when a rotorcraft is in a low airspeed condition. During takeoff or go-around, an aural alert is provided to the pilot before the aircraft slows to less than the effective translational lift speed. The aural, visual, and/or tactile alert gets the pilot's attention to manage the aircraft's airspeed before it is too late in this critical flight phase.Type: ApplicationFiled: August 14, 2012Publication date: February 20, 2014Inventors: Gary A. Ostrom, Yasuo Ishihara, Steve C. Johnson
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Patent number: 8645008Abstract: A method for presenting the current drift values of an aircraft on a display device in which the drift values are presented in a vector presentation. The length of the drift vector above a predefined threshold value is presented in a manner proportional to the current drift velocity, and the length of the drift vector below the threshold value is presented in a manner disproportionate to the current drift velocity. There is a continuous transition between the two ways of presentation at the threshold value.Type: GrantFiled: September 30, 2011Date of Patent: February 4, 2014Assignee: EADS Deutschland GmbHInventor: Thomas Muensterer
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Patent number: 8630752Abstract: A method and a system are provided for displaying flight information of an aircraft. The system receives at least one user defined airspeed related to flight of the aircraft from a user. A processor calculates the at least one calculated airspeed based on data stored in a memory device. A static position is determined by the processor for the user defined and calculated airspeeds. The difference between the positions developed from the user defined and calculated position is also calculated. A difference indicator is displayed to the user for the difference between each user defined and calculated position.Type: GrantFiled: September 8, 2011Date of Patent: January 14, 2014Assignee: Honeywell International Inc.Inventors: Saravanakumar Gurusamy, Nirupam Karmakar, Pramod Kumar Malviya, Prithvi Krishnamurthy
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Method for dynamic determination of the true mass of a non rigid body subject to low frequency noise
Patent number: 8630753Abstract: A dynamic method to accurately determine the mass of a vehicle which deforms on acceleration and is subject to low frequency noise is disclosed. Only the greater than zero hertz frequencies of the signals are processed. Both signals are squelched during periods of high jerk to reduce the error between true mass and apparent mass. For a single body or combination vehicle such as a semi-rig with a propulsive body of known mass a reference for matched or Wiener filtering is constructed from the noisy signals to filter low frequency noise. A towing vehicle with a fifth wheel mounted on a dedicated load sensing apparatus can, therefore, determine the weight of any semi-trailer towed on any terrain of any inclination and any changing inclination with the greatest precision in the shortest possible time.Type: GrantFiled: April 11, 2012Date of Patent: January 14, 2014Inventor: Bret Edward Cahill -
Patent number: 8626362Abstract: A method for controlling speed of an aircraft in the air. The method compares a variation of the aircraft speed in the air with a variation of the aircraft speed on the ground for an identical period, and detects any significant difference between the variations.Type: GrantFiled: January 18, 2008Date of Patent: January 7, 2014Assignee: AirbusInventor: Sebastien Freissinet
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Patent number: 8620495Abstract: An electronic multi-function probe (MFP) is provided for positioning adjacent an aircraft skin. The electronic MFP includes a plurality of pressure sensing ports and an electronics housing. Positioned within the electronics housing are air data processing circuitry and stall protection system processing circuitry. The air data processing circuitry is configured to generate air data parameters, including airspeed and altitude, as a function of pressures at the plurality of pressure sensing ports. The stall protection system processing circuitry of the electronic MFP is configured to detect stall conditions as a function of angle of attack and at least one air data parameter from the air data processing circuitry, and to generate stall protection system outputs indicative of the detected stall conditions.Type: GrantFiled: December 18, 2007Date of Patent: December 31, 2013Assignee: Rosemount Aerospace Inc.Inventors: Steve F. Alwin, Ronald Fritz Liffrig, Mathew L. Sandnas
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Patent number: 8620532Abstract: Systems and methods for providing passive crowd-sourced alternate route recommendations. In one embodiment, locations of users of a number of mobile location-aware devices are tracked over time. Upon receiving a request, users of mobile location-aware devices that have traveled from a desired start location to a desired stop location are identified. Location histories for the identified users are analyzed to determine one or more different routes taken from the desired start location to the desired stop location. The one or more different routes, or a select subset thereof, are then returned to the requestor as recommended alternate routes.Type: GrantFiled: March 25, 2010Date of Patent: December 31, 2013Assignee: Waldeck Technology, LLCInventors: Scott Curtis, Eric P. Halber, Gregory M. Evans, Steven L. Petersen
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Patent number: 8604942Abstract: Avionics display system is provided for deployment onboard an aircraft and includes an air traffic data source that provides the avionics display system with data indicative of at least position and velocity of a neighboring aircraft. The system comprises a cockpit display system, and a monitor included within the cockpit display system. The cockpit display system receives and displays position and velocity data pertaining to the neighboring aircraft on the cockpit monitor as a position symbol and a velocity vector graphic. A processor operatively coupled to the monitor is configured to generate an air traffic display on the monitor including symbology indicative of (1) the current position of the neighboring aircraft (2) a velocity of the neighboring aircraft, and (3) the rate-of-change of the velocity of the neighboring aircraft.Type: GrantFiled: November 8, 2011Date of Patent: December 10, 2013Assignee: Honeywell International Inc.Inventors: Stephen Whitlow, Jan Flasar, Trent Reusser
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Patent number: 8554539Abstract: A method of performing a morpheme analysis by utilizing additional information is provided. The method includes acquiring an analysis target phrase and additional information associated with the target phrase. A term is obtained form the additional information. And the phrase is analyzed to extract a key term or keyword by using the term extracted from the additional data.Type: GrantFiled: March 30, 2007Date of Patent: October 8, 2013Assignee: NHN CorporationInventor: Taeil Kim
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Patent number: 8552888Abstract: A device calculates a first air speed representing an estimated air speed during flight using measurements of static pressure and total pressure onboard the aircraft. The device includes a storage device for storing in memory, in case of detection of a ground taxiing of the aircraft, the most recently determined value of static pressure corrected from induced aerodynamic effects. As a result, a second air speed representing the estimated air speed during the ground taxiing may be calculated by implementing a correction and using the most recently determined value of static pressure when the ground taxiing of the aircraft is detected. A method for automatically estimating an air speed of an aircraft is also provided.Type: GrantFiled: March 31, 2011Date of Patent: October 8, 2013Assignee: Airbus Operations (SAS)Inventors: Jean-Damien Perrie, Valérie Brivet, Stéphane Saint-Aroman
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Patent number: 8538669Abstract: Methods and apparatus are provided for transmitting incursion alerts to a plurality of in-flight aircraft in accordance with preconfigured pilot preferences. The apparatus comprises a data store module containing data sets against which the pilot preferences are evaluated during flight, including weather, airspace and flight restrictions, ground delay programs, and air traffic information. The apparatus further includes a flight path module containing route and position information for each aircraft. An incursion alert processing module evaluates the flight path, data store, and pilot preferences and generates incursion alerts which are transmitted to each aircraft during flight, either directly or via ground based dispatchers or flight operations personnel.Type: GrantFiled: September 9, 2011Date of Patent: September 17, 2013Assignee: Honeywell International Inc.Inventors: Anand Agarwal, David Brabham, Trip Redner, SatyaBhaskar Payasam
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Patent number: 8538607Abstract: Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.Type: GrantFiled: January 28, 2010Date of Patent: September 17, 2013Assignee: Honeywell International Inc.Inventors: Mark T. Manfred, Thomas A. Ryno
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Patent number: 8527119Abstract: An optimization method and device for a take-off procedure of an aircraft. The device (1) comprising means (2, 10) for determining optimum values for take-off parameters and adapting them for the actual take-off conditions.Type: GrantFiled: August 31, 2010Date of Patent: September 3, 2013Assignee: Airbus Operations (SAS)Inventors: Jérôme Chaptal, Rosa Maria Torres Calderon
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Patent number: 8527233Abstract: The different advantageous embodiments provide an apparatus and method for identifying an airspeed for an aircraft. In one advantageous embodiment, an apparatus is provided. The apparatus consists of a plurality of pitot-static probes. The plurality of pitot-static probes generate a first data. The apparatus also consists of a plurality of angle of attack sensor systems. The plurality of angle of attack sensor systems generate a second data. The apparatus also consists of a plurality of light detection and ranging sensors. The light detection and ranging sensors generates a third data. The apparatus also consists of a signal consolidation system configured to detect errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of light detection and ranging sensors.Type: GrantFiled: September 27, 2010Date of Patent: September 3, 2013Assignee: The Boeing CompanyInventor: Melville Duncan Walter McIntyre
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Publication number: 20130211634Abstract: A system for providing sideslip envelope protection includes a processor for obtaining values of a sideslip envelope indicative of operating conditions of the aircraft along an axis and for estimating a sideslip angle along the axis from at least one operating condition; and a comparer for comparing the sideslip angle with the sideslip envelope to generate an output value, where the processor determines a maximum yaw rate from the output value and scales the maximum yaw rate to generate a scaled yaw rate.Type: ApplicationFiled: February 14, 2012Publication date: August 15, 2013Applicant: SIKORSKY AIRCRAFT CORPORATIONInventor: Igor Cherepinsky
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Publication number: 20130173091Abstract: The invention relates to a method for early detection of the vortex ring state in a helicopter, having the following steps: establishing flight control signals for flight control with regard to the vertical movement axis of the helicopter and detecting resultant movements in the vertical movement axis of the helicopter, and detecting early the vortex ring state of the helicopter in accordance with a correlation between the flight control signals and the vertical movements in the vertical movement axis.Type: ApplicationFiled: July 13, 2011Publication date: July 4, 2013Applicants: OFFICE NATIONAL D'ÉTUDES ET DE RECHERCHES AÉROSPATIALES, DEUTSCHES ZENTRUM FÜR LUFT-UND RAUMFAHRT E.V.Inventors: Max Abildgaard, Laurent Binet
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Patent number: 8457872Abstract: The invention relates to a method for managing the flight of an aircraft flying along a trajectory and being subject to an absolute time constraint (on a downstream point) or relative time constraint (spacing with respect to a downstream aircraft), the said aircraft comprising a flight management system calculating a temporal discrepancy to the said time constraint, wherein the said method includes the following steps: the calculation of a distance on the basis of the temporal discrepancy, the modification of the trajectory: if the temporal discrepancy to the time constraint corresponds to an advance, the lengthening of the trajectory by the distance; if the temporal discrepancy to the time constraint corresponds to a delay, the shortening of the trajectory by the distance.Type: GrantFiled: February 23, 2010Date of Patent: June 4, 2013Assignee: ThalesInventor: Guy Deker
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Patent number: 8451144Abstract: 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: GrantFiled: February 4, 2009Date of Patent: May 28, 2013Assignee: Honeywell International Inc.Inventors: Yasuo Ishihara, Steve Johnson, Kevin J Conner
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Patent number: 8447442Abstract: 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 ratiType: GrantFiled: December 2, 2010Date of Patent: May 21, 2013Assignee: ThalesInventors: Jérôme Sacle, Christophe Caillaud, Lionel Verot
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Patent number: 8437887Abstract: The invention relates to a method for optimizing the fuel consumption of an aircraft during flight. At a given point of the flight, a fuel excess (EXTRA) is determined relative to the statutory loads depending on the flight profile and weather conditions forecast for the rest of the flight. If the excess (EXTRA) is less than a given value (EXTRA-mini), for at least one of the forthcoming flight phases ({circle around (1)}, {circle around (2)}, {circle around (3)}), the speed of the aircraft is adjusted so as to increase the excess (EXTRA).Type: GrantFiled: November 22, 2006Date of Patent: May 7, 2013Assignee: ThalesInventor: François Bernard René Coulmeau
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Patent number: 8433460Abstract: An onboard sensor suite generally includes two main components: a proximity sensor suite for measuring the projectile muzzle velocity; and a pressure sensor suite for measuring the projectile airspeed. The flight velocity of the projectile can then be estimated with a high degree of accuracy using either the muzzle velocity by itself or the airspeed by itself, or, in a preferred embodiment, by using both the muzzle velocity and the airspeed. The proximity sensor suite includes proximity sensors that are mounted along a projectile body; a wire harness; and an onboard computer or CPU. The pressure sensor suite includes a Pitot pressure transducer and two static pressure transducers that are mounted within the projectile body; a wire harness; and a CPU.Type: GrantFiled: November 10, 2010Date of Patent: April 30, 2013Assignee: The United States of America as Represented by the Secretary of the ArmyInventors: Thomas Recchia, Wilfredo Toledo, Jason Cahayla, Eric Scheper
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Patent number: 8428812Abstract: A running locus generating apparatus 1 for generating a future running locus of a vehicle driven by a hybrid scheme comprises constraint condition computing means 30 for convergently computing a constraint condition including at least a road boundary condition and evaluation function computing means 30 for deriving a running locus by a convergent computation with an evaluation function including at least an evaluation of an electric power balance in a hybrid system when the electric power balance is positive in a state where the constraint condition by the constraint condition computing means 30 is satisfied.Type: GrantFiled: October 30, 2008Date of Patent: April 23, 2013Assignee: Toyota Jidosha Kabushiki KaishaInventor: Koji Taguchi
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Publication number: 20130066486Abstract: A method and a system are provided for displaying flight information of an aircraft. The system receives at least one user defined airspeed related to flight of the aircraft from a user. A processor calculates the at least one calculated airspeed based on data stored in a memory device. A static position is determined by the processor for the user defined and calculated airspeeds. The difference between the positions developed from the user defined and calculated position is also calculated. A difference indicator is displayed to the user for the difference between each user defined and calculated position.Type: ApplicationFiled: September 8, 2011Publication date: March 14, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Saravanakumar Gurusamy, Nirupam Karmakar, Pramod Kumar Malviya, Prithvi Krishnamurthy
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Patent number: 8386097Abstract: Disclosed is a method and device for assisting guidance of an aircraft. A flight management system is used to determine guidance instructions that include speed instructions having at least one flight time constraint to guide the aircraft to a check-point. An accuracy level for complying with the flight time constraint and at least one error level for at least one flight parameter are generated by an accuracy generating unit. An operating margin for at least one second parameter is determined from the determined accuracy and error levels, with the operating margin being representative of air speed criterion values of the aircraft. A range determining unit is used to determine whether the range of air speed criterion values is within an air speed envelope of the aircraft, and the speed instructions are modified when the range of air speed criterion values is not within the air speed envelope.Type: GrantFiled: March 11, 2008Date of Patent: February 26, 2013Assignee: Airbus Operations SASInventors: Jean-Louis de Menorval, Fabrice Lucas, David Gerasimovic
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Publication number: 20130035809Abstract: According to the invention, the system for determining, in real time, flight parameters of an aircraft, in the course of a flight of the latter, comprises an extended Kalman filter (10) which is configured on the basis of flight mechanics equations establishing a dependency relationship between at least two preselected flight parameters of said aircraft to be estimated and which is formed so as to deliver, during a flight of said aircraft, joint estimations of said selected flight parameters.Type: ApplicationFiled: July 31, 2012Publication date: February 7, 2013Applicants: ONERA (Office National d'Etudes et de Recherches Aerospatiales), AIRBUS OPERATIONS (SAS)Inventors: Pierre EZERZERE, Cédric SEREN, Georges HARDIER