Modeling and verifying method of laser gyroscope temperature compensation model

A laser gyroscope and temperature compensation technology, which is applied to Sagnac effect gyroscopes, instruments, measuring devices, etc., can solve the problems of inability to meet the requirements of inertial navigation equipment and the reduction of the accuracy of laser gyroscopes

Active Publication Date: 2017-02-01
TIANJIN NAVIGATION INSTR RES INST
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Problems solved by technology

The laser gyroscope is sensitive to changes in ambient temperature. When the ambient temperature changes, the accuracy of the laser gyroscope wil

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  • Modeling and verifying method of laser gyroscope temperature compensation model
  • Modeling and verifying method of laser gyroscope temperature compensation model
  • Modeling and verifying method of laser gyroscope temperature compensation model

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Embodiment Construction

[0046] The following describes the embodiments of the present invention in further detail with reference to the accompanying drawings:

[0047] The present invention firstly generates a temperature cycle in the range of -20°C to +50°C through the temperature test box during the modeling test of the temperature compensation model of the laser gyroscope to obtain the coefficient of the temperature term in the temperature compensation model; then the temperature test box is used The internal temperature changes are circulated at the speeds of ±2℃ / min, ±1℃ / min, ±0.5℃ / min, ±0.2℃ / min, ±0.1℃ / min, and get the temperature compensation model related to the temperature change rate Coefficients and coefficients related to the coupling terms of temperature and temperature change rate; finally, a set of verification tests weakly related to the laser gyroscope temperature compensation model modeling test are established, from the dual indicators of laser gyroscope bias stability and bias repeata...

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Abstract

The invention relates to a modeling and verifying method of a laser gyroscope temperature compensation model. The method comprises 1, acquiring original data output by a laser gyroscope and multiple temperature information in different positions, building a laser gyroscope temperature compensation model and calculating a temperature compensation coefficient, and 2, building a verifying test weakly related to a modeling test on the laser gyroscope temperature compensation model and verifying compensation effects of the temperature compensation model through dual indexes such as the laser gyroscope zero-bias stability and zero-bias repeatability. The method realizes simultaneous examination and verification of two zero-bias key indexes such as zero-bias stability and zero-bias repeatability of the laser gyroscope after temperature compensation, has a more clear temperature compensation object and is conducive to further improvement of a temperature compensation precision. The method is conducive to improvement of a temperature coefficient precision of a temperature compensation model so that a temperature compensation precision and reliability are improved.

Description

Technical field [0001] The invention belongs to the technical field of laser gyroscope temperature compensation, in particular to a method for modeling and verifying a laser gyroscope temperature compensation model. Background technique [0002] Laser gyroscopes are currently inertial sensitive components commonly used in medium and high precision inertial navigation equipment. Laser gyroscopes are sensitive to changes in ambient temperature. When the ambient temperature changes, the accuracy of laser gyroscopes is significantly reduced, even more than an order of magnitude, which will not be able to meet the requirements of inertial navigation equipment. Therefore, temperature compensation for the laser gyroscope is necessary, and the accuracy of temperature compensation directly affects the accuracy of the inertial navigation device. Summary of the invention [0003] The purpose of the present invention is to overcome the shortcomings of the prior art and provide a method for m...

Claims

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Application Information

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IPC IPC(8): G01C19/64G01C25/00
CPCG01C19/64G01C25/005
Inventor 于堃徐凯张群孙玥张世先
Owner TIANJIN NAVIGATION INSTR RES INST
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