Design And Verification Of Inertial Navigation Performance Testing System Based On Satellite Navigation

Inertial navigation has attracted much attention as an important modern military navigation mode,and its performance testing is also crucial.With the upgrading of military weapons and the complexity of the working environment,especially for equipments such as intercontinental ballistic missile and submarine,once the performance of the inertial navigation system fails to meet the requirements or break down,it will have a serious impact on the weapon system.The traditional test turntable can not simulate the working environment of inertial navigation exactly,and is too dependent on the turntable,so it is difficult to meet the INS test under complex conditions.In recent years,the accuracy of satellite navigation is constantly improving,especially the rapid development of precision positioning,which provides the possibility of satellite navigation applied to inertial navigation performance testing.Satellite navigation technology has the advantages of low-cost,high-accuracy and allweathercompared with traditional measurement technology.In view of the disadvantages of traditional inertial navigation test method,the design of inertial navigation performance testing system based on satellite navigation is studied in this paper.The research work is carried out as follows:(1)Analyze the advantage of satellite navigation aided inertial navigation performance test compared with traditional test methods.Based on a traditional partial ambiguity fixing method,the accuracy performance of satellite navigation precision positioning is studied,and the feasibility of using satellite navigation to measure ins performance parameters is illustrated.(2)Aiming at the characteristics of existing turntable test and flight test,a conception of inertial navigation performance testing system based on runway is put forward.This paper illustrates the performance parameters of inertial navigation system that can be measured by runway test system and its applicable scope.The overall architecture of the test system is proposed,including the requirement of test parameters,the target of the system design,the composition of the runway system,the hypothesis of system conditions,and the requirement of the measurement method.The role and implementation requirements of satellite navigation in the whole system are also analyzed.Finally,the test error and precision range of the runway system is analyzed.(3)The design and implementation technology of runway test system is studied.The appropriate track model is constructed by using 3DMAX technology,and the reference system and deformation monitoring of the track are analyzed.The corresponding test schemes for the position related and attitude related inertial navigation parameters are put forward respectively.The software for satellite navigation attitude measurement based on MATLAB GUI is developed,and the accuracy of the attitude measurement and the limitations of this method are illustrated by the simulation experiment.This paper also analyzes the high-speed photography technology used to measure the runway system,and puts forward a attitude measurement method based on the orbit position.Finally,the data flow direction and its processing are discussed.(4)Based on the measurement results provided by GPS,the inertial navigation parameter simulation experiment is carried out,which mainly test the location,speed and acceleration of SINS.The GPS measurement part is achieved bysemi physical simulation using the satellite signal simulator.The SINS part designs the MATLAB GUI software to do a simulationbased on orbit track.Finally,through the data processing of the simulation results,it is verified that the SINS performance test based on GPS measurement results is feasible.