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- W2356586642 abstract "Recently,the integrated navigation using star tracker in missiles and rockets becomes a hotspot in both domestic and oversea.The integrated navigation method of SINS/Star with large view field star tracker is studied and the Kalman filter equation is established in this paper.Using the SINS error transfer matrix method,the navigation error of ballistic missile in ascend phase is also estimated.The simulation results show that the integrated navigation method of SINS/Star with large view field star tracker can revise attitude angle error and gyroscope constant drift while the velocity and position error in ascend phase can also be estimated." @default.
- W2356586642 created "2016-06-24" @default.
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- W2356586642 date "2011-01-01" @default.
- W2356586642 modified "2023-09-28" @default.
- W2356586642 title "The Research on Integrated Navigation Method of SINS/Star with Large View Field Star Tracker" @default.
- W2356586642 hasPublicationYear "2011" @default.
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