Error Analysis of Strapdown Inertia Navigation System in Tactical Missiles

被引：1
|
作者：
Zhang Long-jie [1 ]
Xie Xiao-fang [1 ]
Li De-dong [1 ]
Wang Yan [1 ]
机构：
[1] Naval Aeronaut & Astronaut Univ, Dept Ordnance Sci & Technol, Yantai 264001, Peoples R China
来源：
CEIS 2011 | 2011年 / 15卷
关键词：
Tactical Missile; Strapdown Inertial Navigation System; Error Model; System Simulation;
D O I：
10.1016/j.proeng.2011.08.270
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
To clarify the navigation error of strapdown inertial navigation system( SINS) with low navigation accuracy, short working period, and fickle operating environment that installed in tactical missiles, a new navigation error model of SINS was established. Founded by a six dimensional kinematic model of tactical missile and a three dimensional target model, the paper rebuilt the whole course of tactical missile attacking the moving target, where correlative output parameters were used to calculate the navigation error model of SINS simultaneously. Experiment result revealed the influence of different error sources to navigation errors of SINS, which is constructive to the improvement of navigation accuracy of SINS. (C) 2011 Published by Elsevier Ltd. Selection and/or peer-review under responsibility of [CEIS 2011]
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页数：5
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