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2009 WRI World Congress on Computer Science and Information Engineering
Multi-sensor Information Fusion for Aircraft Attitude Determination System
Los Angeles, California USA
March 31-April 02
ISBN: 978-0-7695-3507-4
A multi-sensor information fusion based aircraft attitude determination system is investigated. Firstly, A scheme of the aircraft attitude determination system including multiple sensors is designed, in which gyroscope measures the angular velocity, the strap-down accelerometer measures the acceleration, the magnetic heading meter measures the yaw angle, and the GPS measures the velocity. Secondly, the measurement models of the multiple sensors are described. Thirdly, an information fusion filtering algorithm which is equal to Kalman filtering is derived based on information fusion estimation theory, and is used to obtain the attitude estimation and the velocity estimation of the aircraft by fusing all the measurement information. Finally, the simulation results show the feasibility and the effectiveness of the proposed aircraft attitude determination system.
Index Terms:
Information Fusion, Attitude Determination System, Estimation, Filtering
Citation:
Zhen Ziyang, Wang Zhisheng, Hu Yong, "Multi-sensor Information Fusion for Aircraft Attitude Determination System," csie, vol. 6, pp.474-478, 2009 WRI World Congress on Computer Science and Information Engineering, 2009
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