Enhanced Accuracy Navigation Solutions Realized Through SINS/GPS Integrated Navigation System

被引：0
|
作者：
Fariz, Outamazirt [1 ]
Ushaq, Muhammad [2 ]
Yan, Lin [1 ]
Li, Fu [1 ]
机构：
[1] Beihang Univ, Sch Automat Sci & Elect Engn, 37 Xue Yuan Lu, Beijing 100191, Peoples R China
[2] Beihang Univ, Sch Instrumentat Sci & Optoelectron Engn, Beijing 100191, Peoples R China
来源：
OPTIROB 2013: OPTIMIZATION OF THE INTELLIGENT SYSTEMS AND THEIR APPLICATIONS IN AEROSPACE, ROBOTICS, MECHANICAL ENGINEERING, MANUFACTURING SYSTEMS, BIOMECHATRONICS AND NEUROREHABILITATION | 2014年 / 332卷
关键词：
Inertial Navigation; Integrated Navigation; GPS; Kalman Filtering;
D O I：
10.4028/www.scientific.net/AMM.332.79
中图分类号：
TH [机械、仪表工业];
学科分类号：
0802 ;
摘要：
Strapdown Inertial Navigation Systems (SINS) displays position errors which grow with time in an unbounded manner. This degradation is due to the errors in the initialization of the inertial measurement unit, and inertial sensor imperfections such as accelerometer biases and gyroscope drifts. Improvement to this unbounded growth in errors can be made by updating the inertial navigation system solutions periodically with external position fixes, velocity fixes, attitude fixes or any combination of these fixes. The increased accuracy is obtained through external measurements updating inertial navigation system using Kalman filter algorithm. It is the basic requirement that the inertial data and data from the external aids be combined in an optimal and efficient manner. In this paper an efficient method for integration of Strapdown Inertial Navigation System (SINS), Global Positioning System (GPS) is presented using a centralized linear Kalman filter.
引用
收藏
页码：79 / 85
页数：7
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