Abstract
An attitude determination system composed of gyroscopes, accelerometer and magnetometer is designed. An extended Kalman filter was used for estimating aircraft’s state. The attitude can be determined via data fusion technique. The experimental results indicate that this combination could effectively restrain attitude error arising from the random drift of sensors. The system has the characteristics of small size, low cost and good reliability.
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Ye, X., Zhu, L., Changyin, S., Wang, W. (2013). An Attitude Determination System of Quad-rotor Aircraft Based on Extended Kalman Filter and Data Fusion Technique. In: Sun, C., Fang, F., Zhou, ZH., Yang, W., Liu, ZY. (eds) Intelligence Science and Big Data Engineering. IScIDE 2013. Lecture Notes in Computer Science, vol 8261. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-42057-3_96
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DOI: https://doi.org/10.1007/978-3-642-42057-3_96
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-42056-6
Online ISBN: 978-3-642-42057-3
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