The research of high accuracy autonomous navigation in the satellite orbit maneuver

Autonomous integrated navigation algorithm based on the GPS navigation system-assisted is studied aiming at the condition that the inertial navigation system error is gradually increased with the expansion of reckoning time. The inertial device mathematical model of random drift and inertial navigation system error equation are established through the analysis of the inertial properties of the system error sources. The filter of the inertial/GPS navigation is designed, which realizes the drift compensation of the inertial device. The valid arithmetic of the integrated navigation system and practicable technical case are proved through simulation. The research provides theoretical principles and practicable references to the realization of the satellite precision navigation.