Research On Calibration Of SINS By Kalman Filter

Inertial devices are the most important part of an aircraft.Strapdown inertial navigation systems have many advantages which are widely used in aircraftsin place of platform inertial groups.However,the error parameters of inertial sensors in the inertial group will change irregularly with time.In order to solve the problem of drift of the inertial error parameter,the most effective method is to calibrate it periodically.There are three main methods of calibration.The first is the traditional method of decommissioning the aircraft’s inertial group from the body and then performing calibration at a specific laboratory site through a precision three-axis turntable.This method has the advantages of high accuracy and small volume of the inertial group,but the operation is cumbersome,takes a long time,and the guarantee is poor.The second method is self-calibration through the internal inertial group with a rotating mechanism.Although the protection is greatly improved,it also brings the disadvantages of high cost and large inertial group.The third method is the entire aircraft calibration method.It is applicable to small and medium-sized aircrafts and does not require many complicated equipments,greatly improving the force security.This topic adopts the third method,and proposes a calibration technique that does not disassemble the inertial group on the aircraft,and can estimate the error parameters of the inertial component in real time under the premise that the inertial group and the aircraft are not separated.This method can reduce the calibration cost of the IMU,reduce the length of the calibration,and has extremely important significance for the improvement of combat effectiveness and force support.