Algorithms for estimation of parameters of micromechanical gyros

Abstract

Purpose

The purpose of this paper is to present and demonstrate the efficiency of utilization of a new approach for estimating parameters of micromechanical gyros (MMG) during their operation. It is shown that the main sources of errors are due to the following three factors: measurement errors of micron deviations of the sensitive element, unknown actual value of difference between the frequencies of primary and secondary oscillations and unknown value of damping constant for the axis of secondary oscillations. The estimation of the last two factors during the operation leads to a significant increase of accuracy of MMG. The solution of the problem is presented in the current paper.

Design/methodology/approach

To solve this problem, an original two-level algorithm intended for use in the embedded MMG controller is considered. The identification of the internal MMG parameters is carried out at the first stage. At the second stage, an MMG model is created, based on the results of identification of parameters at the first stage. This model is used as a basis for synthesis of a Kalman filter for estimating the angular velocity. The ways of simplifying identification algorithms and filtering for the purpose of their practical implementation are shown.

Findings

This paper presents the research results on the effectiveness of the proposed algorithms. Results of simulation are used to confirm the effectiveness of the proposed algorithm in reducing the effect of changes in the design parameters of MMG on the accuracy of the angular velocity measurements.

Practical implications

Proposed algorithms can be used in embedded MMG controllers.

Originality/value

This paper presents a new approach for improving the accuracy of MMG by using a built-in algorithm for estimating parameters during system operation.

Citation

Panferov, A.I. and Ponomarev, V. (2015), "Algorithms for estimation of parameters of micromechanical gyros", Aircraft Engineering and Aerospace Technology, Vol. 87 No. 6, pp. 557-562. https://doi.org/10.1108/AEAT-08-2014-0125