Analysis of Filtering Methods for the SINS/CNS Integrated Navigation System of Missile Motion

被引：0
|
作者：
Zhang, Dan [1 ]
Fu, Kui [1 ]
Ge, Shuzhi Sam [1 ]
Tang, Zhong-Liang [1 ]
He, Wei [1 ]
机构：
[1] Univ Elect Sci & Technol China, Inst Robot, Chengdu 611731, Peoples R China
来源：
2014 11TH WORLD CONGRESS ON INTELLIGENT CONTROL AND AUTOMATION (WCICA) | 2014年
关键词：
Autonomous integrated navigation; Celestial navigation system; Strapdown inertial navigation system;
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
In this paper, we investigate the problem of autonomous integrated navigation of strapdown inertial navigation system (SINS)/celestial navigation system (CNS) for a ballistic missile. To handle the nonlinear missile dynamic model, three filtering methods including extended Kalman filter (EKF), extended Kalman particle filter (EKPF) and unscented particle filter (UPF) are utilized to fusion the integrated navigation system and improve the navigation accuracy. The performance of the navigation system based on the three methods is analyzed and compared. Simulation results indicate that the UPF can provide the highest navigation accuracy with the price of highest computation burden.
引用
收藏
页码：3854 / 3859
页数：6
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