REALIZATION OF GPS／SST／SINS INTEGRATED NAVIGATION FILTER ALGORITHM FOR BALLISTIC MISSILE

Considering the domestic single navigation system of the ballistic missile, a new filter method is presented. The method integrates the information of the strapdown star tracker (SST) attitude, the position and the velocity of a high speed GPS with a strapdown inertial navigation system (SINS) information into one filter, thus improving the precision of the attitude, the velocity, and the position. Finally, the GPS/SST/SINS simulation platfornt is designed. Simulation results demonstrate that the filter is robust and reliable, and the precision rises to the comparative level abroad.