Research On Fault Detection And Isolation Technology Of Multi-Instrument Redundancy Laser Gyro Inertial Measurement System

Rocket has the characteristics of long orbit,orbit more tasks,laser gyro inertial measurement system(The following is called IMU)as an important navigation component carrier rocket control system,for the arrows on the control system of speed,the position and posture information carrier.In order to improve the arrow laser dynamic adaptability and reliability of the IMU,in the process of the flight to laser IMU for fault detection and isolation,this topic is based on the table more redundant laser IMU research,through to the laser IMU internal fault instrument online fault detection,realize the fault isolation after instrument reconstructs the redundant information,so as to realize the normal output of laser IMU navigation information,does not affect the navigation precision of rocket flight.Firstly,by analyzing the working principle of multi-table redundant laser inertial group,the calibration coefficient error,installation error and normal deviation of the system are modeled.The specific failure mode of laser inertial group is identified,the fault model is established and the on-line fault simulation is carried out.Second,determine the fault detection using the method of equivalent space,analyzes the IMU pulse laser after the quantitative influence on fault detection,the method of using three-channel filter can solve the problem of quantification of fault detection,and through the Monte Carlo method to determine the threshold three-channel threshold.Finally,the system has the function of fault detection and isolation through simulation test,so that the laser inertial group can still navigate normally when there is fault.