[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

Journal of Projectiles, Rockets, Missiles and Guidance >

2014 , Vol. 34 >Issue 5: 29 - 32

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2014.05.008

MISSILES AND GUIDANCE TECHNOLOGY

Online Calibration Method of Missile-borne SINS/CNS Integrated Navigation System

  • YANG Gongliu ,
  • WANG Lifen ,
  • YANG Shujie
Expand
  • 1 School of Instrumentation Science and Opt-electronics Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
    2 National Key Laboratory of Inertial Technology, Beijing 100191, China

Received date: 2013-08-09

  Online published: 2025-05-30

Fold

Abstract

An online calibration method of missile-borne SINS/CNS integrated navigation system was presented. This method augments the star sensor's installation angle error, gyro drift and accelerometer's bias error as quantity of state, the relationship between star sensor and attitude angle of inertial navigation system is used to establish observation equation, Kalman filter is used to estimate and compensate the installation error of CNS and the inertial instrument error. Motion path tending to general state was designed for simulation and validation of above methods. Simulation results show that this method can estimate the star sensor installation errors and inertial component error with the installation error estimation accuracy better than 0.1′, gyro drift estimation accuracy better than 0.01°/h, accelerometer bias estimation accuracy better than 20 µg.

Key words： SINS/CNS integrated navigation; online calibration; star tracker; installation error

Cite this article

YANG Gongliu , WANG Lifen , YANG Shujie . Online Calibration Method of Missile-borne SINS/CNS Integrated Navigation System[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2014 , 34(5) : 29 -32 . DOI: 10.15892/j.cnki.djzdxb.2014.05.008

[an error occurred while processing this directive]

References

[1]
杨波, 王跃钢, 单斌, 等. 长航时环境下高精度组合导航方法研究与仿真[J]. 宇航学报, 2011, 32(5): 1054-4059- .
[2]
吴海仙, 俞文伯, 房建成. 高空长航时无人机 SINS/CNS 组合导航系统仿真研究[J]. 航空学报, 2006, 27(2): 299-304.
[3]
卫育新, 白俊卿. 车载 SINS/DR 组合导航系统的在线标定方法[J]. 中国惯性技术学报, 2009, 17(6): 651-653.
[4]
Carl Christian Liebe. Star trackers for attitude determination[J]. IEEE Aerospace and Electronic Systems Magazine, 1995, 10(6): 10-16.
[5]
黄德鸣, 程禄. 惯性导航系统[M].北京: 国防工业出版社, 1986.
[6]
胡倩倩, 曾庆化, 宋国安, 等. 一种数据融合车载捷联惯导系统在线标定方法[J]. 计算机仿真, 2012, 29(8): 336-340.
Options
Outlines

/

〈 〉

[an error occurred while processing this directive]