Federated Information Fusion Technology for SINS/CNS/SMNS Integrated Navigation System

The integrated principle of SINS/CNS/SMNS is investigated, and a federated information fusion method for the integrated navigation system is founded. On account of primary navigation errors of SINS aroused by the errors of initial position, attitude alignment and inertia sensors, a novel independent navigation scheme of using CNS and SMNS to update SINS is proposed. When the cruise missile had been flying 25 km off the earth´s surface, making use of the measurement information of CNS, the mathematical platformpsilas error angles of SINS were deduced. Then, utilizing optimum estimation theory, the gyroscope drifts have been acquired, and accumulated errors of velocity and position are updated. At the end of flight-path, in order to ulteriorly correct the errors of SINS, utilizing SMNS to acquire the real-time image, it had been matched with the stored reference image of corresponding region in computer. The simulating results show that the federated information fusion of using CNS and SMNS to revise SINS is reasonable and feasible, and this independent integrated navigation system can satisfy high precise navigation demand of cruise missiles.