Patents by Inventor Christian Lignon
Christian Lignon 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).
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Patent number: 11662207Abstract: Inertial measurement apparatus arranged to be carried by a carrier vehicle include a chassis, a turntable mounted on the chassis, a first inertial measurement unit mounted on the turntable and connected to an electronic control unit connected to a motor for controlling turning of the turntable, and a second inertial measurement unit secured to the chassis. The control unit turns the turntable through one revolution with periodic alternating motion from a fixed initial angular position of the turntable. The control unit calculates the acceleration of the carrier vehicle from measuring the first inertial measurement unit while the turntable is stationary and from measuring the second inertial measurement unit while the turntable is moving. The control unit reconstitutes an inertial reference frame for each inertial measurement unit and compares the two inertial reference frames to determine a difference and takes account of this difference when calculating the acceleration.Type: GrantFiled: November 20, 2019Date of Patent: May 30, 2023Assignee: SAFRAN ELECTRONICS & DEFENSEInventors: Christian Lignon, Philippe Elie, Sylvain Faure
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Patent number: 11486708Abstract: A method and a device resets an inertial unit of a transport on the basis of information delivered by a viewfinder of the transport. According to one embodiment: a horizontal velocity vector of the transport and coordinates of the transport are obtained from the inertial unit, a horizontal line of sight of the viewfinder is obtained on at least one landmark, coordinates of at least one landmark are obtained, an angle between the horizontal velocity vector and the horizontal line of sight is computed, the drift of the computed angle is computed, an error is computed on the basis of the obtained coordinates, the computed angle and its computed drift, and the computed error is transferred to a Kalman filter for filtering the error and resetting the inertial unit.Type: GrantFiled: May 25, 2020Date of Patent: November 1, 2022Assignee: SAFRAN ELECTRONICS & DEFENSEInventor: Christian Lignon
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Publication number: 20220205790Abstract: A method and a device resets an inertial unit of a transport on the basis of information delivered by a viewfinder of the transport. According to one embodiment: a horizontal velocity vector of the transport and coordinates of the transport are obtained from the inertial unit, a horizontal line of sight of the viewfinder is obtained on at least one landmark, coordinates of at least one landmark are obtained, an angle between the horizontal velocity vector and the horizontal line of sight is computed, the drift of the computed angle is computed, an error is computed on the basis of the obtained coordinates, the computed angle and its computed drift, and the computed error is transferred to a Kalman filter for filtering the error and resetting the inertial unit.Type: ApplicationFiled: May 25, 2020Publication date: June 30, 2022Applicant: SAFRAN ELECTRONICS & DEFENSEInventor: Christian LIGNON
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Patent number: 11371848Abstract: A method of characterizing an inertial measurement unit includes a block carrying one accelerometer positioned on an axis of a measurement reference frame and having one gyro arranged to determine the orientation of the frame relative to an inertial reference frame. The method includes keeping the inertial measurement unit centered on a point that is stationary relative to the ground and that is in a predetermined environment, to obtain accelerometer signals that are images of at least one component of the specific force vector in the measurement reference frame and also gyro signals that are images of at least one component of the instantaneous rotation of the measurement reference frame; processing the signals to obtain data representative of projecting of the specific force vector into the inertial reference frame, after compensating for rotation of the Earth; and calculating Allan variance on the data and comparing it with reference data.Type: GrantFiled: December 19, 2019Date of Patent: June 28, 2022Assignee: SAFRAN ELECTRONICS & DEFENSEInventors: Philippe Elie, Frédéric Davi, Christian Lignon
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Publication number: 20220042803Abstract: A method of characterizing an inertial measurement unit includes a block carrying one accelerometer positioned on an axis of a measurement reference frame and having one gyro arranged to determine the orientation of the frame relative to an inertial reference frame. The method includes keeping the inertial measurement unit centered on a point that is stationary relative to the ground and that is in a predetermined environment, to obtain accelerometer signals that are images of at least one component of the specific force vector in the measurement reference frame and also gyro signals that are images of at least one component of the instantaneous rotation of the measurement reference frame; processing the signals to obtain data representative of projecting of the specific force vector into the inertial reference frame, after compensating for rotation of the Earth; and calculating Allan variance on the data and comparing it with reference data.Type: ApplicationFiled: December 19, 2019Publication date: February 10, 2022Inventors: Philippe ELIE, Frédéric DAVI, Christian LIGNON
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Publication number: 20210356274Abstract: Inertial measurement apparatus arranged to be carried by a carrier vehicle include a chassis, a turntable mounted on the chassis, a first inertial measurement unit mounted on the turntable and connected to an electronic control unit connected to a motor for controlling turning of the turntable, and a second inertial measurement unit secured to the chassis. The control unit turns the turntable through one revolution with periodic alternating motion from a fixed initial angular position of the turntable. The control unit calculates the acceleration of the carrier vehicle from measuring the first inertial measurement unit while the turntable is stationary and from measuring the second inertial measurement unit while the turntable is moving. The control unit reconstitutes an inertial reference frame for each inertial measurement unit and compares the two inertial reference frames to determine a difference and takes account of this difference when calculating the acceleration.Type: ApplicationFiled: November 20, 2019Publication date: November 18, 2021Inventors: Christian LIGNON, Philippe ELIE, Sylvain FAURE
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Publication number: 20160116302Abstract: A method for comparing two inertial guidance systems which are integral with a carrier in positions that are separated from one another and which each comprise three angular measurement sensors and three accelerometric sensors mounted along the axes of a measurement reference frame specific to each inertial guidance system, the method comprising the steps for: over a pre-determined period of time, measuring a specific force and rotations respectively with the accelerometric sensors and the angular sensors of each inertial guidance system, correcting for a cantilever effect in order to bring the reference frames to the same origin, reconstructing an inertial reference frame for each inertial guidance system using the specific force and rotations thus measured, comparing the inertial reference frames in order to determine a separation between them.Type: ApplicationFiled: December 23, 2013Publication date: April 28, 2016Inventors: Christian LIGNON, Nicolas GENDRE
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Patent number: 9279682Abstract: An inertial unit comprising an inertial core (3) that is connected to a control unit (50) and that includes three gyros (9, 10, 11) that are mounted relative to one another so as to have sensing axes (X, Y, Z) that are substantially perpendicular to one another, the gyros being vibrating axisymmetric gyros with hemispherical resonators, the unit being characterized in that the core is mounted on a carousel (2) arranged to drive the inertial core in rotation about an axis of rotation (4) at at least one frequency that corresponds to a minimum for spectral error density of the gyros. An angle-measurement method making use of the unit.Type: GrantFiled: May 23, 2013Date of Patent: March 8, 2016Assignee: SAGEM DEFENSE SECURITEInventors: Alain Renault, Christian Lignon, Etienne Brunstein
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Patent number: 9217640Abstract: A gyroscopic system provides measurements on the basis of a vibrating gyroscope and provides a measurement signal. A periodic control signal is applied to it; in order to rotate the position of vibration, during a half period, according to a first speed profile, from a first up to a second position; and in order to rotate the position of vibration in an opposite direction during the other part of the period, according to a second speed profile, up to a third position. The measurements are based on corrected signals, each of said corrected signals, respectively for each of the vibrating gyroscopes, being obtained by; deducting the control signal from the measurement signal of the vibrating gyroscope; and taking account of errors identified on the basis of a comparison of the measurements provided by the gyroscopic system as a function of the position of vibration with reference measurements.Type: GrantFiled: April 18, 2011Date of Patent: December 22, 2015Assignee: SAGEM DEFENSE SÉCURITÉInventors: Christian Lignon, Yannick Foloppe
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Patent number: 9103672Abstract: Gyroscopic measurements are provided, by a system comprising a vibrating gyroscope, in the form of an output signal. The vibrating gyroscope provides an original measurement signal. A periodic control signal (CP) is applied to it over a time period, which signal is suitable: for rotating the geometric position of vibration in a first direction, during a part of the time period; and for rotating the geometric position of vibration in a second direction opposite to the first direction, during the other part of the time period; said control signal having a zero mean over said time period and exhibiting portions of signal at high frequency relative to the output signal; said output signal being based on a corrected signal emanating from the original measurement signal; in which the corrected signal is based on an identification of errors made during the signal portions at high frequency.Type: GrantFiled: April 18, 2011Date of Patent: August 11, 2015Assignee: SAGEM DEFENSE SÉCURITÉInventor: Christian Lignon
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Patent number: 8725415Abstract: A long-term navigation method using an inertial unit associated with a system of axes X, Y, Z and mounted on a vehicle traveling relative to the Earth in order to measure its movements relative to an inertial frame of reference having axes Xi, Yi, and Zi. The method includes the steps of acting in permanent manner to measure an orientation of the system of axes X, Y, Z in the inertial frame of reference and applying a predetermined sequence of turnovers to the inertial unit in the inertial frame of reference about first and second axes that are substantially perpendicular to each other and in such a manner that at the end of the sequence the inertial unit is in a final orientation identical to its initial orientation relative to the inertial frame of reference, with the turnovers canceling within the sequence.Type: GrantFiled: October 19, 2010Date of Patent: May 13, 2014Assignee: Sagem Defense SecuriteInventor: Christian Lignon
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Publication number: 20130312518Abstract: An inertial unit comprising an inertial core (3) that is connected to a control unit. (50) and that includes three gyros (9, 10, 11) that are mounted relative to one another so as to have sensing axes (X, Y, Z) that are substantially perpendicular to one another, the gyros being vibrating axisymmetric gyros with hemispherical resonators, the unit being characterized in that the core is mounted on a carousel (2) arranged to drive the inertial core in rotation about an axis of rotation (4) at at least one frequency that corresponds to a minimum for spectral error density of the gyros. An angle-measurement method making use of the unit.Type: ApplicationFiled: May 23, 2013Publication date: November 28, 2013Inventors: Alain RENAULT, Christian LIGNON, Etienne BRUNSTEIN
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Publication number: 20130031978Abstract: Gyroscopic measurements are provided, by a system comprising a vibrating gyroscope, in the form of an output signal. The vibrating gyroscope provides an original measurement signal. A periodic control signal (CP) is applied to it over a time period, which signal is suitable: for rotating the geometric position of vibration in a first direction, during a part of the time period; and for rotating the geometric position of vibration in a second direction opposite to the first direction, during the other part of the time period; said control signal having a zero mean over said time period and exhibiting portions of signal at high frequency relative to the output signal; said output signal being based on a corrected signal emanating from the original measurement signal; in which the corrected signal is based on an identification of errors made during the signal portions at high frequency.Type: ApplicationFiled: April 18, 2011Publication date: February 7, 2013Applicant: SAGEM DEFENSE SECURITE'Inventor: Christian Lignon
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Publication number: 20130031948Abstract: A gyroscopic system provides measurements on the basis of a vibrating gyroscope and provides a measurement signal. A periodic control signal is applied to it; in order to rotate the position of vibration, during a half period, according to a first speed profile, from a first up to a second position; and in order to rotate the position of vibration in an opposite direction during the other part of the period, according to a second speed profile, up to a third position. The measurements are based on corrected signals, each of said corrected signals, respectively for each of the vibrating gyroscopes, being obtained by; deducting the control signal from the measurement signal of the vibrating gyroscope; and taking account of errors identified on the basis of a comparison, of the measurements provided by the gyroscopic system as a function of the position of vibration with reference measurements.Type: ApplicationFiled: April 18, 2011Publication date: February 7, 2013Applicant: SAGEM DEFENSE SECURITE'Inventors: Christian Lignon, Yannick Foloppe
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Patent number: 8342024Abstract: A gyroscopic system supplies measurements on the basis of a vibratory gyroscope, which vibrates in a first vibration position and supplies a measurement signal. A periodic command signal is applied to it over a time period to cause the vibration geometrical position to turn a first way during one part of the time period, causing a change in accordance with a first speed profile from the first position to a second position; and to cause the vibration geometrical position to turn a second way opposite the first way during the other part of the time period, causing a change in accordance with a second speed profile from the second position to the first position. The speed profiles indicate a speed variation of the change of position. The measurements supplied by the system are then based on a corrected signal obtained by subtracting the command signal from the measurement signal supplied by the gyroscope.Type: GrantFiled: October 19, 2009Date of Patent: January 1, 2013Assignee: Sagem Defense SecuriteInventor: Christian Lignon
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Publication number: 20120203456Abstract: A long-term navigation method using an inertial unit associated with a system of axes X, Y, Z and mounted on a vehicle traveling relative to the Earth in order to measure its movements relative to an inertial frame of reference having axes Xi, Yi, and Zi. The method includes the steps of acting in permanent manner to measure an orientation of the system of axes X, Y, Z in the inertial frame of reference and applying a predetermined sequence of turnovers to the inertial unit in the inertial frame of reference about first and second axes that are substantially perpendicular to each other and in such a manner that at the end of the sequence the inertial unit is in a final orientation identical to its initial orientation relative to the inertial frame of reference, with the turnovers canceling within the sequence.Type: ApplicationFiled: October 19, 2010Publication date: August 9, 2012Inventor: Christian Lignon
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Patent number: 7997134Abstract: A gyroscopic system is disclosed comprising at least a vibrating gyroscope, as a first mechanism of angle measurement, designed to provide a first measurement of angle values according to a measurement axis; and a second mechanism of angle measurement, designed to provide a second measurement of angle values according to said measurement axis. First angle values through the first angle measurement mechanism vibrating in a current vibration position and second angle values through the second angle measurement mechanism are provided simultaneously; and from these second angle values corrected on the basis of a comparison of the first and second angle values are deduced. Then the vibration position of the first angle measurement mechanism is changed from the current position to another vibration position.Type: GrantFiled: April 10, 2008Date of Patent: August 16, 2011Assignee: Sagem Defense SecuriteInventors: Christian Lignon, Arnauld Carre
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Publication number: 20100095771Abstract: A gyroscopic system supplies measurements on the basis of a vibratory gyroscope, which vibrates in a first vibration position and supplies a measurement signal. A periodic command signal is applied to it over a time period to cause the vibration geometrical position to turn a first way during one part of the time period, causing a change in accordance with a first speed profile from the first position to a second position; and to cause the vibration geometrical position to turn a second way opposite the first way during the other part of the time period, causing a change in accordance with a second speed profile from the second position to the first position. The speed profiles indicate a speed variation of the change of position. The measurements supplied by the system are then based on a corrected signal obtained by subtracting the command signal from the measurement signal supplied by the gyroscope.Type: ApplicationFiled: October 19, 2009Publication date: April 22, 2010Applicant: SAGEM DEFENCE SECURITEInventor: Christian Lignon
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Publication number: 20090158846Abstract: A gyroscopic system is disclosed comprising at least a vibrating gyroscope, a first means of angle measurement, designed to provide a first measurement of angle values according to a measurement axis; and—a second means of angle measurement, designed to provide a second measurement of angle values according to said measurement axis. First angle values through the first angle measurement means vibrating in a current vibration position and second angle values through the second angle measurement means are provided simultaneously; and from these second angle values corrected on the basis of a comparison of the first and second angle values are deduced. Then the vibration position of the first angle measurement means is changed from the current position to another vibration position.Type: ApplicationFiled: April 10, 2008Publication date: June 25, 2009Applicant: Sagem Defense SecuriteInventors: Christian Lignon, Arnauld Carre
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Patent number: 7327461Abstract: A push-pull method of controlling a laser gyro. At least three mirrors form a closed-loop light path for two laser beams propagating in opposite directions, which is subjected to movement. At least two of the mirrors are associated with actuators connected to push-pull control members for controlling the positions of the mirrors to minimize the amplitude of the winking signal which occurs in a lased intensity signal of the laser beams. The method includes detecting the frequency of the winking signal of at least one laser beam, and of triggering the measurement of the amplitude of the winking signal when the frequency of the winking signal is less than a predetermined threshold corresponding to passing into a dead band of the gyro.Type: GrantFiled: April 13, 2005Date of Patent: February 5, 2008Assignee: Sagem SAInventor: Christian Lignon