Research On Sins/Star Integrated Navigation Technology

Modern aircraft need autonomous navigation system that has high precision andhigh reliability. Many countries focus on the aircraft that can fly highly long timebecause of its advantage in the field of all-weather, remote flying. It can fly highly forlonger time. Account to its flying in complex environment, so it needs high precision andhigh autonomy. SINS/Star integrated navigation system uses two information sources toget complementary advantages. It can provide precision and reliability navigation resultsin addition to high autonomy.This paper studies the SINS/Star Integrated Navigation several key issues, the maincontents are summarized as follows:According to the limitation of the traditional star tracker autonomous positioning,this paper puts forward a novel navigation and localization method of rapid stellarhorizon atmospheric refraction using the least squares differential correction method, andgives the theoretical analysis of the localization precision of the novel stellar navigationand localization method. This stellar localization method uses the characteristics of thestellar horizon atmospheric refraction, and does not need the dynamics model of theaircraft or any other knowledge. Furthermore, the mathematical method is easy andreliable, while the localization precision is high.In allusion to the emanative position of SINS/Star attitude integrated system, thispaper puts forward a new method of SINS/Star integrated navigation system: attitude andposition integrated system. By contrast, the simulation results show that the proposedalgorithm can acquire accurate attitude and position than the system of attitude integrated,and it can comprehensive the navigation error coming from inertial device, so there is notany emanative position.According to the application of aircraft that can fly highly long time, this paper putsforwards a new autonomy navigation program:‘Three-Stage navigation program’, whichcan meet the requirement of the navigation system of the aircraft that can fly highly longtime.In allusion to the data synchronization problem, this paper puts forwards a datasynchronization method of SINS/Star integrated navigation system by usingextrapolation method which can give a virtual and accurate SINS result of the fusionmoment. The data synchronization method can improve the accuracy of SINS/Starintegrated navigation system.