Error Correction Capability of GPS/INS Integrated Navigation System for Guided Rockets-Reference-Cited by-同舟云学术

Error Correction Capability of GPS/INS Integrated Navigation System for Guided Rockets

Published:2013-06 Issue: Volume:325-326 Page:1053-1057
ISSN:1662-7482
Container-title:Applied Mechanics and Materials
language:
Short-container-title:AMM

Author:

Bian Wei Wei¹,Wang Liang Ming¹,Ding Chuan Bing²,Zhong Yang¹

Affiliation:

1. Nanjing University of Science and Technology

2. China Ship Development and Design Center

Abstract

In order to improve the guidance accuracy of long-range rockets, a GPS/INS integrated navigation method with combination of position, velocity and attitude was applied. The GPS/INS integrated navigation system taking the position and velocity from INS and attitude from GPS as observables was studied. The error model of system was established and the Kalman filter was designed. A 6-DOF trajectory simulation was put forward and the correction capability of the INS measurement error by using GPS attitude measurement information was analyzed. The simulation results verify the feasibility and effectiveness of the integrated navigation method.

Publisher

Trans Tech Publications, Ltd.

Link

https://www.scientific.net/AMM.325-326.1053.pdf

Reference7 articles.

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