The Test System Design On The Measurement Unit Of Laser Gyro Strapdown Inertial

This paper is based on a project of a military product, mainly researchingon the calibration and navigation test theory of Strapdown Inertial MeasurementUnit’s(SIMU) of Ring Laser Gyro(RLG). Test mode and methods are established,calibration and navigation software is programmed, and data collection circuitdesigned. Lastly the RLG SIMU’s test system is accomplished.Calibration and navigation test are important to the study and manufactureof the RLG SIMU’s. In this paper, the basic theory and errors of RLG andQuartz Flexibility Tilting Accelerometer(QFTA) are presented, and thedifference between inertial component error and system error is showed.Furthermore, the operational principle and error composing of SIMU are detaileddescribed. The scale factor error, bias and fixed error of the inertial system aredefined, and calibration error model equation is established, which leads toseveral testing methods. The fittest methods, single-rate calibration and twenty-four-position calibration, are decided out of that. The error model of pureinertial navigation is presented on the basis of the mathematical theory of SINS,and static test method is chose with the request of a missile.In this paper, the software and hardware design of the test system isspecified, among which the data collecting circuit and software design process isemphasized. When the whole system design is finished, the test system hasfunctions of data collecting, calibration test, navigation test and automatic flowcontrol, and is used in a SIMU of RLG.In the end of this paper, the results of the test system are analyzed. With aSIMU of RLG, the practical tests of data collecting, calibration and staticnavigation are completed. Testing results show that the functions of the testsystem can fulfill the requests of the SIMU.