Abstract: A measurement of a vibrating inertial sensor disposed on a carrier and includes a resonator extending around two mutually perpendicular x and y axes defining an xy sensor frame of reference and comprising: at least one vibrating movable mass comprising at least two portions configured to vibrate in phase opposition in a direction x? defining an x?y? wave frame of reference, with the vibration wave forming an electrical angle ? relative to the x-axis; at least a pair of excitation transducers and a pair of detection transducers operating along the two axes x and y; the correction method being applied when the sensor is operating with a vibration wave vibrating along the x?-axis and comprising the following steps, when the carrier is substantially stationary: A commanding an electrical rotation of the vibration wave according to a commanded angular velocity ?c, such that the electrical angle ? scans at least one angular range of k? radians; then B retrieving the measured angular values ?e measured by the inerti

Abstract: A hybridized system for measuring the attitude of a wearer, the system includes a satellite positioning system; a measurement unit comprising at least one gyrometer; electronics for calculating the attitude information of the wearer from the information originating from the satellite positioning system and the measurement unit. The hybrid system comprises calculation electronics comprising a means for calculating an angular radius of protection, that is to say an angular radius such that the risk that the error between the calculated attitude and the true attitude of the wearer is not included within this radius is less than a given probability, the radius being equal to the sum of two contributions, the first contribution being equal to positioning errors linked to the measurement unit, the second contribution being equal to positioning errors linked to the satellite positioning system.

Abstract: An inertial reference unit includes a first measurement channel comprising: a first high-performance inertial measurement unit comprising first measurement means for measuring specific forces and first measurement means for measuring angular velocities, a first computing unit able to compute pure inertial data based on the measurements of the first measurement unit; a second measurement channel comprising: a second inertial measurement unit of performance lower than the first inertial measurement unit, comprising second measurement means for measuring specific forces and second measurement means for measuring angular velocities; a second computing unit able to compute pure inertial data based on the measurements of the second measurement unit; an integrity check function able to implement a method for checking the integrity of the data of the first measurement channel based on the data provided by the second measurement channel; a synchronization means for synchronizing the measurements of the first and secon

Abstract: A hybridized system for measuring the attitude of a wearer, the system includes a satellite positioning system; a measurement unit comprising at least one gyrometer; electronics for calculating the attitude information of the wearer from the information originating from the satellite positioning system and the measurement unit. The hybrid system comprises calculation electronics comprising a means for calculating an angular radius of protection, that is to say an angular radius such that the risk that the error between the calculated attitude and the true attitude of the wearer is not included within this radius is less than a given probability, the radius being equal to the sum of two contributions, the first contribution being equal to positioning errors linked to the measurement unit, the second contribution being equal to positioning errors linked to the satellite positioning system.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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

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