SINS/GPS Integrated Navigation System for Aerospace Application
- Paper number
IAC-07-B2.I.13
- Author
Dr. Du Yaling, Beijing Aerospace Automatic Control Institute, China
- Coauthor
Dr. Gao Xiaoying, Beijing Aerospace Automatic Control Institute, China
- Coauthor
Mr. Cao Ju, Beijing Aerospace Automatic Control Institute, China
- Coauthor
Mr. Liu Jizhong, Beijing Aerospace Automatic Control Institute, China
- Year
2007
- Abstract
The developments of Global Positioning System (GPS) provide new instruments for space application. This paper presents a new integrated navigation project for aerospace application. The hardware of integrated navigation system includes one Strapdown Inertial Navigation System (SINS), three GPS receivers and one navigation computer. Three GPS receivers not only can measure the carrier’s speed and position, but also can provide the attitude information. If the Integrated Navigation system applies the platform attitude errors as the approximate body attitude errors to get attitude measure equations, which will bring some errors to system. This paper analyses the difference of the platform attitude and the body attitude, deduces the attitude measure equations in detail. To take the application into account, this paper presents the observations vector pretreatment and attitude measure equations, to improve the attitude integrated algorithm. The improvement reduces the approximate math former errors, and realized easily. Simulation shows that the novel SINS/GPS integrated navigation system improves the precision and reliability of the navigation system effectively, well continuity and real-time capability. It provides an effective way for aerospace application.
- Abstract document
- Manuscript document
IAC-07-B2.I.13.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.