The Research Of Integrated Navigation And Realatuive Position Estimate Methord In The Satellites

The main purpose of this study is to solve the problem of the SINS/GPS was used in the satellite and work out the relative navigation between the satellites and how the differential GPS was work.Due to the error of the inertial navigation was augmented following the time postpone. It cannot be used for long period navigation. So it cannot be used as a navigation system singleness, it must be auxiliared by the other navigation system. And in the early time many integrated navigation error model was come into being. In all of them the model derivated by Britting and Widnall was the representative. This model was based on the Earth Centered Earth Fixed (ECEF) Frame.Considering the error of the system and the error of the sensor,the error model of the system usually adopted the position velocity and gesture as state variable make up state equation. In this study the shortage of the traditional inertial navigation was posed and analysis. In order to make sure the spacecraft can fly in any condition here adopted the error model was derived by Friedland in 1978, which was based on the Earth Centered Inertial (ECI) Frame. And make it combination with the GPS buildup a new assembled navigation system. At last make the arithmetic simulation of the error model.Hill equation was often used in the relative navigation between the satellites. But the classical Hill equation was restricted by the condition of the initialization. When the condition of the initialization cannot meet, the level orientation will appear volatilization and cannot match with the practice. While for the target of the not cooperated wants to make it satisfied with the condition of the initialization every time is nearly impossible. So this study adopted the improved Hill equation and proved the arithmetic was feasible by the computer simulation. Though the Hill equation was improved it cannot satisfied with the long distance navigation. Here is considering the main satellite the following satellite and the target satellite format a triangle in the space which was useful in the relative navigation. The orbit of the following satellite was resolved by calculate the Hill equation. At last make an analysis the error from the simulation of the system.Differential GPS is the commonly used in the navigation but it normally used in...