Abstract: The errors of strapdown inertial navigation system(SINS) were chosen as states of the integrated system.The attitude matrix outputs from SINS and charge coupled device(CCD) starsensor were used to construct the observation,and the algorithm of SINS/CCD integrated navigation was designed.The velocity outputs and position outputs from SINS and global positioning system(GPS) were used to construct the observation,and the algorithm of SINS/GPS integrated navigation was designed.Then by the federated Kalman filtering,local optimal estimations of system states from the local filters were passed to the master filter,and the master filter can give the global optimal estimates of states through the global optimal fusion algorithm.Simulation results show that SINS/CCD/GPS integrated navigation system had high navigation accuracy,with the positioning accuracy up to 3.5 meters,and the azimuth accuracy up to 9 angle seconds,which was very fit for the precise navigation for aerocrafts.