Satellite/pseudolite/INS integrated navigation algorithm

To meet the urgent demand of a high precision, high reliability landing guidance system for carrier-based aircraft landing safely, the satellite/pseudolite/inertial navigation system (INS) integrated landing navigation technology is studied. Based on the geometric dilution of precision (GDOP) calculation, the layout scheme of pseudolites on the ship and the navigation message structure are proposed. The satellite/pseudolite/INS integrated landing guidance algorithm is studied by using satellite and pseudolites dual differential carrier phase information, and the dual differential ambiguity is solved by using the improved least-squares ambiguity decorrelation adjustment (LAMBDA) iterative algorithm. Through establishing filtered equation based on the carrier aircraft movement model, landing target motion information can be calculated. Finally, highly accurate navigation information can be obtained by fusing the inertial navigation data. The simulation results show that the lateral positioning error of the proposed satellite/pseudolite/INS integrated landing navigation technology is less than 0.3 m, and longitudinal positioning error is less than 0.1 m, and the height positioning error is less than 0.3 m, which can meet the requirements of carrier-based aircraft landing. Compared with the satellite/inertial guidance algorithm, it greatly improves the positioning accuracy in the vertical direction, which is extremely important to ensure a safe landing. Furthermore, the proposed landing guidance technology is not only high-precision, but also reliable and continuous operation, anti-jamming capability, which is significant to the protection of carrier-based aircraft landing safety.