Systems Engineering and Electronics
Previous Articles Next Articles
WANG Wei, GUO Huijie, MENG Yue
Online:
Published:
Abstract:
To meet the urgent demand of a high precision〖JP〗, high reliability landing guidance system for carrierbased 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 leastsquares 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 carrierbased 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 highprecision, but also reliable and continuous operation, antijamming capability, which is significant to the protection of carrierbased aircraft landing safety.
WANG Wei, GUO Huijie, MENG Yue. Satellite/pseudolite/INS integrated navigation algorithm[J]. Systems Engineering and Electronics, doi: 10.3969/j.issn.1001-506X.2017.02.24.
0 / / Recommend
Add to citation manager EndNote|Reference Manager|ProCite|BibTeX|RefWorks
URL: https://www.sys-ele.com/EN/10.3969/j.issn.1001-506X.2017.02.24
https://www.sys-ele.com/EN/Y2017/V39/I2/391