Airborne Inertial & Celestial Integrated Navigation Technology And Simulation

This dissertation focuses on the integrated navigation technologies of airborne Inertial Navigation (INS) and Celestial Navigation (CNS). And pertinent simulation experiments are committed to verify the conclusions educed in this dissertation.As the primary navigation system in the most of airplanes, INS has a problem of error accumulation, which must be corrected to improve the measurement accuracy. Research shows the integrated navigation is the best way to solve this problem. Up to now, the widely used integrated navigation systems are the integrations of INS & satellite navigation, which could be easily jammed in wartime usages. However, integration of INS & CNS can reduce the error accumulation of INS and also strengthen the anti-jamming ability of the navigation system, owing to the strong anti-electromagnetic-jamming ability and high accuracy in attitude of the CNS.Based on the general discussed of the error transmission processes and properties of INS, the error accumulation problem caused by the Gyro Drift is specially analyzed. The key technologies in CNS are discussed in this dissertation, and the algorithms of Star-Map Simulation and Matching Identification in CNS are particularly developed. Ultimately, an INS & CNS integrated navigation simulation system is built with the RT-LAB real-time distributed simulation platform to verify the theoretically analyzed results, in which the Kalman filtering technique is used to calibrate the Gyro Drift.The simulation experiments results show that the Gyro Drift is the main source of the error accumulation in INS and the developed algorithms of Star-Map Simulation and Matching Identification in CNS are more suitable for the airborne applications. The simulation experiments results also verify that the INS & CNS integrated navigation system built in this dissertation can achieve higher measurement accuracy and possesses strong anti-jamming ability in the actual combats backgrounds.