Gyroscopic measurement method and sensor

The gyroscopic measurement method and sensor address measurement errors by controlling the sensor's alternating rotation with stable forces, reducing harmonic errors and enhancing precision in angular velocity determination.

FR3160460B1Active Publication Date: 2026-04-10THALES SA
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Patent Information

Application Number
FR2024002970
Authority / Receiving Office
FR · FR
Patent Type
Patents
Current Assignee / Owner
Filing Date
2024-03-25
Publication Date
2026-04-10
Estimated Expiration
2044-03-25

AI Technical Summary

Technical Problem

Existing gyroscopic measurement methods suffer from measurement errors due to defects in the conversion of control signals to electrostatic forces, leading to non-zero average errors over the sensor's alternating rotation, particularly in harmonic errors and scale factor errors, which are not effectively mitigated by existing calibration techniques.

Method used

A gyroscopic measurement method and sensor that controls the alternating rotation of pilot and detection modes using a stable force to minimize harmonic errors, employing a calibration process involving a first force in phase with the pilot mode vibrations and a second force in quadrature phase, allowing for the estimation of the actual force applied without disturbing the sensor's measurement, and determining the instantaneous angular velocity based on reference and measured vibrations.

Benefits of technology

The method reduces measurement errors, particularly the scale factor error, by stabilizing the force applied to the sensor, enabling accurate determination of angular velocity without relying on unstable controlled signals, thus improving measurement precision.

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Abstract

Measurement method and gyroscopic sensor The present invention relates to a sensor (10) comprising a housing (12) and a vibrating element (15) capable of vibrating relative to the housing (12), comprising: an initialization (410), to provide a pilot amplitude (xmax), a detection amplitude (ymax), an adjustment control (Tth) of predetermined spectral signature, and an angular velocity calibration (Ωcal);a calibration (420), comprising the control of the pilot amplitude and the vibration detection amplitude of the vibrating element (15) along the direction (x) of the pilot mode and the direction (y) of the detection mode, and simultaneously the exercise of a first stable force (Fy,phase,suppapp) configured so as not to disturb the measurement of the sensor (10) from the adjustment command (Tth), as well as the exercise of a second force (Fy,quadapp) determined on the basis of the spectral signature of the adjustment command to cause a rotation of the direction of the pilot mode, an instantaneous angular velocity (Ω(t)) of the housing (12) being imposed equal to the calibration angular velocity (Ωcal), and the determination of a reference angular velocity (Ωref); an acquisition (430), analogous to the calibration but with a free instantaneous angular velocity (Ω(t)); a determination (440) of a measured instantaneous angular velocity (Ωmes(t)). Figure for the abbreviation: 3;
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