A General Euler Angle Error Model of Strapdown Inertial Navigation Systems

被引：5
|
作者：
Li, Jianli [1 ,2 ]
Dang, Pengfei [2 ]
Li, Yiqi [2 ]
Gu, Bin [2 ]
机构：
[1] China Elect Technol Grp Corp, Res Inst 54, Natl Key Lab Satellite Nav Syst & Equipment Techn, Shijiazhuang 050002, Hebei, Peoples R China
[2] Beihang Univ, Sch Instrument Sci & Optoelect Engn, Beijing 100191, Peoples R China
来源：
APPLIED SCIENCES-BASEL | 2018年 / 8卷 / 01期
基金：
国家高技术研究发展计划(863计划); 中国国家自然科学基金;
关键词：
attitude error model; navigation error propagation; relative Euler angle error; convected Euler angle error; FLIGHT COARSE ALIGNMENT; INITIAL ALIGNMENT; I APPLICATION; SINS; EQUATIONS;
D O I：
10.3390/app8010074
中图分类号：
O6 [化学];
学科分类号：
0703 ;
摘要：
Attitude error models play an important role in analyzing the characteristics of navigation error propagation for the design and operation of strapdown inertial navigation systems (SINS). However, the majority of existing attitude error models focus on misalignment, rather than Euler angle errors. Misalignment cannot directly describe attitude error propagation, which is an indirect measurement. To solve the problem, a general Euler angle error model of SINS is proposed. Based on Euler angle error propagation analysis, relative Euler angle errors, and convected Euler angle errors are introduced to compose the general Euler angle error model. Simulation experiments are carried out to verify the proposed model.
引用
收藏
页数：18
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