Patents by Inventor Jacques Coatantiec

Jacques Coatantiec has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 10094932
    Abstract: The invention relates to a method and a device for verifying the integrity of position vector information obtained by at least two satellite geolocation devices, each of the geolocation devices being able to receive a plurality of wireless signals from a plurality of separate satellites, and to use the received wireless signals to compute a position vector of said geolocation device, including position coordinates computed in a predetermined spatial reference at a given moment in time, each of the geolocation devices being independent of the other geolocation devices, the satellites used being able to be different from one geolocation device to the next.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: October 9, 2018
    Assignee: THALES
    Inventors: Roland Bonel, Jacques Coatantiec, Sebastien Francois Philippe Legoll
  • Publication number: 20180275283
    Abstract: A method of calculating a speed of an aircraft, a method for calculating a protection radius, a positioning system and an associated aircraft are disclosed. In one aspect, the method includes obtaining a measured speed of the aircraft and obtaining a measured position of the aircraft, associated with a reliability protection radius related to position. The method also includes calculating, by a correction loop, a corrected speed, wherein the calculation of the corrected speed includes calculating a calculated position by integration of the corrected speed, and correcting the measured speed as a function of a difference between the calculated position and the measured position. The method further comprising calculating a reliability protection radius related to the corrected speed.
    Type: Application
    Filed: March 21, 2018
    Publication date: September 27, 2018
    Inventors: Pierre-Yves Dumas, Christian Mehlen, Jacques Coatantiec
  • Patent number: 9828111
    Abstract: Estimating the speed of an aircraft estimates three components of the speed vector (TAS, AOA, SSA) of an aircraft relative to the surrounding air. The static pressure is estimated on the basis of measurements of geographical altitude. A first intermediate variation of a linear combination of the three components of the speed vector of the aircraft relative to the surrounding air is estimated using explicitly the fact that the pressure measured by the static probe is falsified by a known quantity under the effect of the three components of this speed vector of the aircraft relative to the surrounding air. The process then estimates the three components of the speed vector of the aircraft relative to the air by likening the latter to the speed vector of the aircraft relative to an inertial reference frame and by using inertial measurements. The various estimates are fused to provide a final result.
    Type: Grant
    Filed: July 10, 2015
    Date of Patent: November 28, 2017
    Assignee: Thales
    Inventors: Christian Mehlen, Jacques Coatantiec
  • Patent number: 9726499
    Abstract: Method of determining at least one radius of protection associated with a respective navigation parameter of a hybrid inertial navigation system by Kalman filtering employing introduction of a position bias into the state model of the Kalman filter representing the uncertainty associated with the reference safe position.
    Type: Grant
    Filed: November 5, 2015
    Date of Patent: August 8, 2017
    Assignee: Thales
    Inventors: Jacques Coatantiec, Nicolas Vercier
  • Patent number: 9550579
    Abstract: Method of estimation of the speed of an aircraft relative to the surrounding air, in a reference frame tied to the aircraft estimates an estimated static pressure on the basis of measurements of geographical altitude. The process then estimates a first intermediate variation of the speed of the aircraft relative to the surrounding air using explicitly the fact that the pressure measured by the static probe is falsified by a known quantity under the effect of the speed of the aircraft relative to the surrounding air. Finally, temporal integration of the first intermediate variation of the speed of the aircraft relative to the surrounding air provides an estimated speed of the aircraft relative to the surrounding air.
    Type: Grant
    Filed: July 10, 2015
    Date of Patent: January 24, 2017
    Assignee: Thales
    Inventors: Christian Mehlen, Jacques Coatantiec
  • Publication number: 20160325845
    Abstract: Estimating the speed of an aircraft estimates three components of the speed vector (TAS, AOA, SSA) of an aircraft relative to the surrounding air. The static pressure is estimated on the basis of measurements of geographical altitude. A first intermediate variation of a linear combination of the three components of the speed vector of the aircraft relative to the surrounding air is estimated using explicitly the fact that the pressure measured by the static probe is falsified by a known quantity under the effect of the three components of this speed vector of the aircraft relative to the surrounding air. The process then estimates the three components of the speed vector of the aircraft relative to the air by likening the latter to the speed vector of the aircraft relative to an inertial reference frame and by using inertial measurements. The various estimates are fused to provide a final result.
    Type: Application
    Filed: July 10, 2015
    Publication date: November 10, 2016
    Inventors: Christian Mehlen, Jacques Coatantiec
  • Publication number: 20160325844
    Abstract: Method of estimation of the speed of an aircraft relative to the surrounding air, in a reference frame tied to the aircraft estimates an estimated static pressure on the basis of measurements of geographical altitude. The process then estimates a first intermediate variation of the speed of the aircraft relative to the surrounding air using explicitly the fact that the pressure measured by the static probe is falsified by a known quantity under the effect of the speed of the aircraft relative to the surrounding air. Finally, temporal integration of the first intermediate variation of the speed of the aircraft relative to the surrounding air provides an estimated speed of the aircraft relative to the surrounding air.
    Type: Application
    Filed: July 10, 2015
    Publication date: November 10, 2016
    Inventors: Christian Mehlen, Jacques Coatantiec
  • Publication number: 20160131485
    Abstract: Method of determining at least one radius of protection associated with a respective navigation parameter of a hybrid inertial navigation system by Kalman filtering employing introduction of a position bias into the state model of the Kalman filter representing the uncertainty associated with the reference safe position.
    Type: Application
    Filed: November 5, 2015
    Publication date: May 12, 2016
    Inventors: Jacques Coatantiec, Nicolas Vercier
  • Publication number: 20160091611
    Abstract: The invention relates to a method and a device for verifying the integrity of position vector information obtained by at least two satellite geolocation devices, each of the geolocation devices being able to receive a plurality of wireless signals from a plurality of separate satellites, and to use the received wireless signals to compute a position vector of said geolocation device, including position coordinates computed in a predetermined spatial reference at a given moment in time, each of the geolocation devices being independent of the other geolocation devices, the satellites used being able to be different from one geolocation device to the next.
    Type: Application
    Filed: September 25, 2015
    Publication date: March 31, 2016
    Inventors: Roland Bonel, Jacques Coatantiec, Sebastien Francois Philippe Legoll
  • Publication number: 20150308832
    Abstract: The invention relates to a method for managing altitude data of an aircraft in which a main baro-inertial computation loop is used that uses signals originating from an inertial unit and a standard altitude information item supplied by a main air data reference, and at least one standard altitude information item supplied by a secondary baro-inertial deviation loop respectively using signals from said inertial unit of the main loop and a to standard altitude information item originating from the second air data reference, and a baro-inertial altitude deviation, a vertical speed deviation and accelerometric bias deviation visible on the vertical between the main loop and at least one of said secondary baro-inertial loops are computed.
    Type: Application
    Filed: November 29, 2013
    Publication date: October 29, 2015
    Inventor: Jacques Coatantiec
  • Patent number: 9146322
    Abstract: Hybrid system (1) comprising an elementary hybrid system (2) comprising an extended processing module CALC (100) determining a first protection radius of the hybrid system RHG1, associated with a position quantity G, using a first extended variance/covariance matrix MHYPE1 as a function of a predetermined first false alarm probability PFA1, of a predetermined non-integrity level PNI and of a predetermined first probability PP1 of occurrence of an undetected hardware failure of a satellite positioning receiver.
    Type: Grant
    Filed: September 9, 2010
    Date of Patent: September 29, 2015
    Assignee: THALES
    Inventor: Jacques Coatantiec
  • Patent number: 8878722
    Abstract: Method for determining navigation parameters of an aircraft, characterized in that it consists at least in determining the geographic speed {right arrow over (V)}, expressed in a given local fixed coordinate system {{right arrow over (i)}, {right arrow over (j)}, {right arrow over (k)}}, based on the measurements m, of carrier phase increments ??i of the radio navigation signals originating from a plurality of radio navigation satellites in sight of said aircraft, each of said measurements mi constituting an estimate of the relative speed of said aircraft relative to said satellite projected onto the sight axis linking the aircraft to the satellite, each of said measurements m, being compensated by the apparent radial speed of the satellite.
    Type: Grant
    Filed: February 14, 2012
    Date of Patent: November 4, 2014
    Assignee: Thales
    Inventors: Marc Revol, Jacques Mandle, Alain Bibaut, Jacques Coatantiec
  • Patent number: 8655511
    Abstract: An inertial system measures the attitude of an aircraft consisting at least in determining the angle of pitch and/or the angle of heading and/or the angle of roll of the aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative. A pair of accelerometers to determine the angle of pitch being are disposed on either side of the centre of gravity along an axis substantially merged with the longitudinal axis of the aircraft. A pair of accelerometers to determine the angle of heading are disposed on either side of the centre of gravity along an axis substantially merged with the transverse axis of the aircraft. A pair of accelerometers to determine the angle of roll are disposed on either side of the centre of gravity along a vertical axis perpendicular to the plane formed by the other axes.
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: February 18, 2014
    Assignee: Thales
    Inventors: Marc Revol, Jacques Mandle, Alain Bibaut, Jacques Coatantiec
  • Patent number: 8566033
    Abstract: A method for determining the position of a mobile body at a given instant and for monitoring the integrity of the position of said mobile body includes a step of determining a sustained position at the given instant by adding the integral of the hybrid speed between the preceding instant and the given instant to the position of the mobile body at the preceding instant; a step of determining the sustained protection radius associated with the sustained position by adding the integral of the hybrid speed protection radius between the preceding instant and the given instant to the position protection radius of the preceding instant; a step of determining a better position at the given instant, the better position being: when information from the first positioning device is available, the position associated with a better protection radius, the better protection radius being selected by comparing the intermediate protection radius with the sustained protection radius according to a predetermined selection criteri
    Type: Grant
    Filed: May 28, 2010
    Date of Patent: October 22, 2013
    Assignee: Thales
    Inventors: Pierre-Jérôme Clemenceau, Jacques Coatantiec
  • Publication number: 20130030775
    Abstract: A method for determining the position of a mobile body at a given instant and for monitoring the integrity of the position of said mobile body includes a step of determining a sustained position at the given instant by adding the integral of the hybrid speed between the preceding instant and the given instant to the position of the mobile body at the preceding instant; a step of determining the sustained protection radius associated with the sustained position by adding the integral of the hybrid speed protection radius between the preceding instant and the given instant to the position protection radius of the preceding instant; a step of determining a better position at the given instant, the better position being: when information from the first positioning device is available, the position associated with a better protection radius, the better protection radius being selected by comparing the intermediate protection radius with the sustained protection radius according to a predetermined selection criteri
    Type: Application
    Filed: May 28, 2010
    Publication date: January 31, 2013
    Applicant: THALES
    Inventors: Pierre-Jérôme Clemenceau, Jacques Coatantiec
  • Patent number: 8311728
    Abstract: The invention relates to a navigation system for aircraft comprising inertial sensors, a GNSS receiver and potentially a baro-altimeter. The measurements from the inertial sensors are hybridized with the code and phase measurements from the receiver within a main Kalman filter and, possibly, secondary filters. The said measurements are corrected for several types of errors, notably those due to the passage of the satellite signals through the ionospheric layers. The precision of the determination of the position of the aircraft is greatly improved, both in the horizontal plane and in the vertical direction. This is also the case for the corresponding protection radii, which allows margins to be created in order to satisfy the integrity constraints for the navigation solution.
    Type: Grant
    Filed: February 18, 2009
    Date of Patent: November 13, 2012
    Assignee: Thales
    Inventors: Jacques Coatantiec, Sébastien Juillaguet
  • Publication number: 20120226395
    Abstract: An inertial system measures the attitude of an aircraft consisting at least in determining the angle of pitch and/or the angle of heading and/or the angle of roll of the aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative. A pair of accelerometers to determine the angle of pitch being are disposed on either side of the centre of gravity along an axis substantially merged with the longitudinal axis of the aircraft. A pair of accelerometers to determine the angle of heading are disposed on either side of the centre of gravity along an axis substantially merged with the transverse axis of the aircraft. A pair of accelerometers to determine the angle of roll are disposed on either side of the centre of gravity along a vertical axis perpendicular to the plane formed by the other axes.
    Type: Application
    Filed: February 29, 2012
    Publication date: September 6, 2012
    Applicant: THALES
    Inventors: Marc Revol, Jacques Mandle, Alain Bibaut, Jacques Coatantiec
  • Publication number: 20120212369
    Abstract: Method for determining navigation parameters of an aircraft, characterized in that it consists at least in determining the geographic speed {right arrow over (V)}, expressed in a given local fixed coordinate system {{right arrow over (i)}, {right arrow over (j)}, {right arrow over (k)}}, based on the measurements m, of carrier phase increments ??i of the radio navigation signals originating from a plurality of radio navigation satellites in sight of said aircraft, each of said measurements mi constituting an estimate of the relative speed of said aircraft relative to said satellite projected onto the sight axis linking the aircraft to the satellite, each of said measurements m, being compensated by the apparent radial speed of the satellite.
    Type: Application
    Filed: February 14, 2012
    Publication date: August 23, 2012
    Applicant: Thales
    Inventors: Marc Revol, Jacques Mandle, Alain Bibaut, Jacques Coatantiec
  • Publication number: 20120004846
    Abstract: The present invention relates to an air navigation device with inertial sensor units and radio navigation receivers, and is characterized in that its radio navigation receivers are multiple-constellation receivers and in that their output data are hybridized with the data from the inertial sensor units. According to another feature of the invention, at least some of the inertial sensor units are of MEMS type.
    Type: Application
    Filed: May 21, 2007
    Publication date: January 5, 2012
    Applicant: THALES
    Inventors: Jacques Coatantiec, Charles Dussurgey
  • Publication number: 20110084874
    Abstract: Hybrid system (1) comprising an elementary hybrid system (2) comprising an extended processing module CALC (100) determining a first protection radius of the hybrid system RHG1, associated with a position quantity G, using a first extended variance/covariance matrix MHYPE1 as a function of a predetermined first false alarm probability PFA1, of a predetermined non-integrity level PNI and of a predetermined first probability PP1 of occurrence of an undetected hardware failure of a satellite positioning receiver.
    Type: Application
    Filed: September 9, 2010
    Publication date: April 14, 2011
    Applicant: THALES
    Inventor: Jacques Coatantiec