Ballistic missile SINS/CNS integrated navigation method

被引：0
作者：
Qian H. [1 ]
Lang X. [1 ]
Qian L. [2 ]
Peng Y. [3 ]
Wang H. [4 ]
机构：
[1] College of Automation, Harbin Engineering University, Harbin
[2] School of Computer Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing
[3] Beijing Aerospace Automatic Control Institute, Beijing
[4] School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing
来源：
Qian, Huaming (qianhuam@sina.com) | 1600年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 43期
基金：
中国国家自然科学基金;
关键词：
Apparent height; Atmospheric refraction model; Kalman filter; Navigation error; Starlight refraction;
D O I：
10.13700/j.bh.1001-5965.2016.0390
中图分类号：
学科分类号：
摘要：
Considering that traditional strap-down inertial/celestial integrated navigation system (SINS/CNS) cannot accurately estimate the accelerometer bias, which can cause the divergence of navigation errors, a strap-down inertial/celestial integrated navigation method based on the stellar refraction (SINS/RCNS) was proposed. The starlight refraction angle obtained from the stellar sensor and the apparent height obtained from atmospheric refraction model were combined to inhibit the divergence of position error. A novel measurement equation based on stellar refraction was developed and the relationship between the number of used refraction stars and navigation accuracy was analyzed. When multiple refraction stars are used, the proposed method can accurately estimate the accelerometer bias so that the position errors can be inhibited completely, and its observability was analyzed. The estimation of the state of system was realized through the Kalman filter. The simulation results indicate that the precision of navigation based on the proposed method is better than that of the traditional method and inhibits the divergence of the position error effectively, which shows the validation of the proposed method. © 2017, Editorial Board of JBUAA. All right reserved.
引用
收藏
页码：857 / 864
页数：7
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