Study of Laser Gyro Temperature Compensation Technique on LINS

Abstract

Laser gyroscope is a high precision optical angular rate sensor. The stability of the Laser gyro output directly affects the navigation accuracy of the laser gyro inertial navigation system (LINS). On base of analyzing the error model of LINS, the temperature compensation model of laser gyroscope is established. The temperature compensation model of the gyro bias is established and the gyro bias is compensated with the method of subsection Hermite interpolation. Data collection and temperature compensation experimentations of the laser gyro in different temperature conditions are designed and completed. The output of the laser gyro is compensated off-line by the gyro pulse compensation model. The gyro bias is recalculated using the compensated gyro calibration data in order to validate the affection of the gyro temperature compensation method. Experiments show that the compensation effect of this temperature compensation method is visible. The laser gyro static output stability is improved more than 3 times at room temperature. Experiments show that this method has high engineering application value.