Error Correction Capability of GPS/INS Integrated Navigation System for Guided Rockets

Wei Wei Bian; Liang Ming Wang; Chuan Bing Ding; Yang Zhong

doi:10.4028/www.scientific.net/AMM.325-326.1053

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 325-326Error Correction Capability of GPS/INS Integrated...

Error Correction Capability of GPS/INS Integrated Navigation System for Guided Rockets

Abstract:

In order to improve the guidance accuracy of long-range rockets, a GPS/INS integrated navigation method with combination of position, velocity and attitude was applied. The GPS/INS integrated navigation system taking the position and velocity from INS and attitude from GPS as observables was studied. The error model of system was established and the Kalman filter was designed. A 6-DOF trajectory simulation was put forward and the correction capability of the INS measurement error by using GPS attitude measurement information was analyzed. The simulation results verify the feasibility and effectiveness of the integrated navigation method.

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Periodical:

Applied Mechanics and Materials (Volumes 325-326)

Pages:

1053-1057

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.325-326.1053

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Online since:

June 2013

Authors:

Wei Wei Bian, Liang Ming Wang, Chuan Bing Ding, Yang Zhong

Keywords:

GPS, Guided Rockets, Integrated Navigation, Kalman Filter (KF), Simulation

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References

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