期刊名称：International Journal of Security and Its Applications
印刷版ISSN：1738-9976
出版年度：2015
卷号：9
期号：9
页码：65-76
DOI：10.14257/ijsia.2015.9.9.07
出版社：SERSC
摘要：The position and velocity errors are divergent of traditional navigation algorithms used in ballistic missile for it cannot estimate the bias of accelerometer precisely. To solve this problem, a novel SINS/CNS integrated navigation algorithm is proposed in this paper, which adds high angle error, azimuth angle error and height error on the basis of the traditional navigation method. As these three values are related to the position of missile, the proposed method can constrain the divergence of navigation errors. Meanwhile, a system model for ballistic missile is deduced. To verify the navigation precision of the proposed algorithm, the observable analysis and simulation experiments are performed. And the results show that the system state of proposed method is observable completely, and the divergence of navigation error can be restrained thoroughly.
关键词：integrated navigation; bias of accelerometer; height angle; azimuth angle
