Abstract: The invention relates to an inertial navigation system for a carrier comprising a core comprising gyroscopic sensors making it possible to determine the angular velocity thereof according to three axes defining a reference trihedron, two of the axes defining a reference plane and the third axis being at right angles to this plane. The device comprises command and control means making it possible to rotate the core about the third axis and to determine the direction of the geographic north on the basis of the information supplied by the gyroscopic sensors and by an accelerometer placed in the reference plane; the rotation of the core being performed with a period for which the value of the Allan variance of the stability error of the gyroscopic sensors is lower than a given value guaranteeing the accuracy with which the direction of the geographic north can be known.

Abstract: A gyroscope comprising a resonant structure and a plurality of transducers configured to drive a vibrational mode in the resonant structure and detect vibrations of the resonant structure, wherein at least one of the plurality of transducers comprises a piezoelectric mono crystal.

Abstract: A gyroscope comprising a resonant structure and a plurality of transducers configured to drive a vibrational mode in the resonant structure and detect vibrations of the resonant structure, wherein at least one of the plurality of transducers comprises a piezoelectric mono crystal.

Abstract: The present invention is concerned with a method of calibrating a vibrating gyroscope.

Abstract: The invention relates to gyroscopic instruments. The method for calibrating the scale factor of an angular velocity sensor or an axisymmetric vibratory gyroscope, which method uses a control amplitude signal, a control precessional signal CP and a control quadrature signal CQ for exciting the vibration of a resonator on a resonant frequency, involves a first step of pre-calibration which consists of measuring and recording an initial scale factor and the value of an initial control signal, and a second step of measuring the value of the current control signal and establishing a scale factor SF that is corrected on the basis of a proportional relationship involving the initial scale factor SF°, the initial value of the control signal Y° and the current value of the control signal Y° according to the formula SF=SF°Y/Y°.

Abstract: Coriolis vibratory gyroscope includes a thin-walled resonator, fastened centrally on a stem located within the resonator; with 4nk holes in a wall of the resonator and arranged around the stem, where “k” is integer, “n” is order of vibration modes, and the angle between adjacent holes is “?/2nk”. The stem is rotationally symmetric and is fastened on a base; electrodes are arranged on the wall for excitation and measurement of vibration modes, with leads passing from the electrodes through the holes; the base has a seating for the resonator stem, and leads pass from the outside of the base through it, the leads being electrically-insulated and sealed relative to the base; the leads which pass through the base are connected to the leads which pass from the electrodes, allowing signals to pass from outside the base, through the base, through the holes in the resonator wall and to the electrodes.

Abstract: An axially symmetrical Coriolis vibratory gyroscope includes a thin-walled resonator with a hemispherical or cylindrical or toroidal form, the resonator being fixed at the center to a support and being formed with openings in that wall of the resonator which is located around the support, the number of openings being determined on the basis of the formula 4nk, where k is an integer, n is the order of oscillation modes, wherein the support has a symmetrical form along the longitudinal axis and is fixed to a base, electrodes are positioned on the wall of the resonator or next to the resonator for exciting and measuring two oscillation modes, a constant amplitude of one of the modes is maintained and a secondary oscillation mode which is sensitive to Coriolis forces is monitored, and the base is provided with a seat for the support of the resonator and with electrically insulated hermetically sealed leads which pass outwards via the base and through the openings in of the resonator.

Abstract: An effective and precise method and system for compensation and measurement of a zero-bias in an axisymmetrical CVG (Coriolis Vibrating Gyroscope) is provided. Principal mode is driven according to an X-axis. Angular velocity is measured through Coriolis mode excitation along Y-axis. The sensitive axis of the gyroscope is reversed by 180 degrees by switching input and sense signals. Vibration is then driven along Y-axis and angular velocity is sensed along X-axis. On each position, after an arbitrary period of time, the gyroscope output is stored. Half-difference in outputs between two opposite position gives angular velocity and zero-bias effect is canceled. Half-sum in outputs between two opposite position gives the zero-bias error.

Abstract: The invention relates to gyroscopic instruments. The method for calibrating the scale factor of an angular velocity sensor or an axisymmetric vibratory gyroscope, which method uses a control amplitude signal, a control precessional signal CP and a control quadrature signal CQ for exciting the vibration of a resonator on a resonant frequency, involves a first step of pre-calibration which consists of measuring and recording an initial scale factor and the value of an initial control signal, and a second step of measuring the value of the current control signal and establishing a scale factor SF that is corrected on the basis of a proportional relationship involving the initial scale factor SF°, the initial value of the control signal Y° and the current value of the control signal Y° according to the formula SF=SF°Y/Y°.

Abstract: The invention relates to gyroscope equipment.