A Modeling and Verification Method of Laser Gyroscope Temperature Compensation Model
A technology of laser gyroscope and temperature compensation, which is applied to Sagnac effect gyroscopes, instruments, measuring devices, etc., can solve the problems of laser gyroscope accuracy reduction and inability to meet the requirements of inertial navigation equipment, so as to improve accuracy and reliability high-speed, well-targeted results
Active Publication Date: 2019-05-24
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 will be significantly reduced, even exceeding an order of magnitude, and will not be able to meet the requirements of inertial navigation equipment.
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[0046] Embodiments of the present invention are described in further detail below in conjunction with the accompanying drawings:
[0047] In the present invention, when the laser gyroscope temperature compensation model modeling test is performed, the temperature cycle in the range of -20°C to +50°C is generated by the temperature test box to obtain the coefficient of the temperature item in the temperature compensation model; and then the temperature test box is used The internal temperature change is cycled at the speed of ±2°C / min, ±1°C / min, ±0.5°C / min, ±0.2°C / min, ±0.1°C / min respectively, and the temperature compensation model is related to the temperature change rate. coefficients and coefficients related to the coupling term of temperature and temperature change rate; finally, by establishing a set of verification tests weakly correlated with the laser gyroscope temperature compensation model modeling test, the dual indicators of laser gyroscope zero bias stability and ze...
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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 modeling and verification method for a laser gyroscope temperature compensation model. Background technique [0002] Laser gyroscopes are 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 will decrease significantly, even exceeding an order of magnitude, which will not meet the requirements of inertial navigation equipment. Therefore, it is necessary to perform temperature compensation on the laser gyroscope, and the accuracy of temperature compensation directly affects the accuracy of inertial navigation equipment. Contents of the invention [0003] The purpose of the present invention is to overcome the deficiencies of the prior art, and provide a model...
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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