Fiber optic gyroscope eight-position calibration method based on rotating mechanism

Abstract

The invention provides a fiber optic gyroscope eight-position calibration method based on a rotating mechanism. The method comprises the following steps of: fastening fiber optic gyroscope components on the table surface of an indexing mechanism, leveling the table surface and side of the indexing mechanism, and ensuring that a gyroscope coordinate system is superposed with an indexing mechanism coordinate system; determining initial position parameters of a carrier through a GPS (global positioning system), and loading the parameters into a navigation computer; preheating by a strapdown inertial navigation system, and acquiring data output by the fiber optic gyroscope and a quartz accelerometer and processing the data; determining a carrier horizontal attitude angle by using the gravity acceleration component of the accelerometer; establishing a fiber optic gyroscope brief error model; designing an eight-position indexing scheme by using the dual-shaft indexing mechanism; and processing the output data of the gyroscope components on each position acquired by a computer through Matlab software, so as to obtain each error parameter of the gyroscope components. By the eight-position calibration method using the indexing mechanism, each error parameter of the fiber optic gyroscope can be exactly calculated; and short-time and high-precision calibration work to the fiber optic gyroscope can be finished under the condition that the carrier attitude is unknown.

Description

(1) Technical field [0001] The present invention relates to a measurement method, in particular to an eight-position calibration method of an optical fiber gyroscope based on a rotating mechanism. (2) Background technology [0002] The calibration of the strapdown inertial navigation system is mainly the calibration of the inertial instruments in the system. The fiber optic gyroscope is the main inertial instrument in the strapdown inertial navigation system. It is the most critical component in the system hardware. The attitude rate of the gyroscope sensitive carrier is directly related to a series of performance indicators of the system. The error of the inertial instrument is the main factor affecting the accuracy of the inertial system. Therefore, improving the precision of the inertial instrument is a necessary condition for the production of a high-precision inertial navigation system. At present, in order to improve the accuracy of inertial instruments, there are ma...

AI Technical Summary

Problems solved by technology

However, with the development of the fiber optic gyro strapdown inertial navigation system, the strapdown inertial navigation system has higher and higher requirements for the fiber optic gyroscope calibration. The traditional calibration method introduces a large indexing mechanism speed error and calibration parameter coupling error. No longer meets the requirements for calibration of high-precision fiber optic gyroscope components

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