INS Performance Test System For High Dynamic Carriers

As an important navigation method,inertial navigation system is extremely important in the application of missiles,submarines and other military equipment that require autonomous navigation.Especially in the environment of missiles,its high dynamic working environment and high precision requirements place high demands on the performance of INS.Therefore,performance testing of the INS is required to ensure the consistency of the INS in the test and actual combat environment.However,the current turntable and centrifuge test methods cannot realistically simulate the environment in which the inertial navigation is used,and it is difficult to meet the requirements of high dynamic testing.With the development of orbital test technology,it is possible to provide a high dynamic environment simulation test for inertial navigation.Therefore,based on the existing track test,this thesis proposes an inertial navigation performance test system for high dynamic carrier.It is capable of simulating the motion characteristics of an inertial real high dynamic environment.The research work carried out in this thesis is as follows:1.The existing inertial navigation test technology and inertial navigation test method are analyzed.In view of the deficiency of the existing inertial navigation test method,the idea of using the track to perform high dynamic test on the inertial navigation is proposed.The overall architecture and measurement method of the test system test system is designed.The system is studied from two aspects of motion simulation system and data measurement.2.The design and implementation of the motion simulation system is studied.According to the analysis of the inertial guidance in the actual high dynamic environment,the orbit model of the motion simulation is designed,and the force of the vehicle running in the orbit is analyzed.The vacuum tube magnetic suspension is proposed as the motion simulation system.The scheme of the magnetic levitation system is studied.The side suspension magnetic levitation is proposed to solve the centrifugal force problem.The vacuum requirements of the vacuum piping system and the realization of the vacuum were studied.Finally,the influence of the aerodynamics on the operation of the vehicle in the vacuum pipeline at high speed is analyzed by simulation to determine the appropriate vacuum setting.3.The system data measurement scheme and data processing scheme were studied.According to the calibration method and the need of data,the measurement scheme and attitude measurement scheme of the vehicle's motion state are studied,and the measurement scheme of the orbit and the error precision index of the track construction and measurement are analyzed.The measurement accuracy of the motion measurement system is analyzed.And error factors and error simulation analysis of time and space method measurements.The data processing architecture of the whole system is proposed,and the processing scheme of measurement data is studied.4.Due to the limited test conditions,actual testing cannot be carried out.This thesis mainly evolves the running process of the vehicle,and simulates the data of the motion state,which can roughly reflect the actual motion.Since the actual high dynamic measurement data of the inertial navigation cannot be obtained,this paper uses the error principle of the inertial device to generate the simulation data of the inertial navigation.According to the set inertial trajectory,the inertial navigation data is generated for the solution analysis.It is feasible to compare the data obtained by the measurement system.