The Design and Completion of No Resource Attitude Measurement Navigation System

As the inertial navigation system(INS) will be accumulated over time, the course angel error can be diverged especially. The structure of SINS/Gravity/Log integrated navigation system was designed based on the current equipment of space tracking ship. 12 dimension of Kalman filter is extended which will correct the error of system calculated. The experiment results shows that the Algorithm designed can efficiently improve the performance and meet the long-endurance, high-precision attitude measurement requirements.