High-order attitude compensation in coning and rotation coexisting environment

With the development of high-accuracy inertial navigation system inertial sensors, such as ring laser gyroscopes and atomic spin gyroscopes, it is increasingly important to improve the strapdown inertial navigation algorithms to match such high-accuracy inertial sensors. For example, the existing in...

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Bibliographic Details
Published in:IEEE transactions on aerospace and electronic systems 2015-04, Vol.51 (2), p.1178-1190
Main Authors: Wang, Maosong, Wu, Wenqi, Wang, Jinling, Pan, Xianfei
Format: Article
Language:English
Subjects:
Accuracy
Algorithm design and analysis
Algorithms
Gyroscopes
Heuristic algorithms
Inertial navigation
Sensors
Taylor series
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Summary:With the development of high-accuracy inertial navigation system inertial sensors, such as ring laser gyroscopes and atomic spin gyroscopes, it is increasingly important to improve the strapdown inertial navigation algorithms to match such high-accuracy inertial sensors. For example, the existing inertial navigation algorithms have not taken into account the triple-cross-product term of noncommutativity error. However, theoretical analysis demonstrates that the ignored triple-cross-product term is nonignorable under coning motion with constant angular rate precession environments. In this paper, a new high-accuracy rotation vector algorithm is proposed for strapdown inertial navigation. The Taylor series about time is used for error analysis and optimization of the new algorithm. General maneuvers and coning motion with constant angular rate precession environments are considered in establishing the coefficient equations in the proposed algorithm. Error drift equations are given after the error compensation. Normalized quaternion under coning motion with constant angular rate precession environments and Savage's severe integrated angular-rate profiles are used to numerically verify the new algorithm. The results indicate that the new high-order attitude updating algorithm can improve inertial navigation accuracy.
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2014.140084