Modeling And Accuracy Assessment On Missile-Borne SINS/Double-Satellite Integrated Navigation System

A Missile-Borne SINS/Double-Satellite integrated navigation system is discussed in this thesis. Instead of sending signal of positioning quest, instrument errors of SINS can be identified and corrected via the range and range rate between the carrier and satellites of "Beidou" Double-Satellite Positioning Navigation System in order to improve the navigation accuracy.The basic theory of SINS/Double-Satellite integrated navigation is lucubrated. The state equations, the state error equations with a common-used model of SINS instrument errors and the observation equations with range and range rate of SINS/Double-Satellite integrated navigation system are presented based on the launch coordinate.A Kalman filter is given to fit the systems. The feedback amendable technique of instrument errors and the accuracy assessment of fall points are also discussed.Simulation of SINS/Double-Satellite integrated navigation system is discussed in detail and the calculate error of simulation is analyzed. The launch parameters and the integrated navigation time's effects on accuracy of fall points are discussed.The simulation results show that accuracy(Circular error probable) of missile fall points is less than 60m with a Double-Satellite receiver and a SINS of one kind when the launch point is on our mainland, the integrated navigation time is 180s~480s after the missile launched, the range error is 3m(1s) and the range rate error is 0.02m/s(1s).