Initial Alignment Error and Navigation Error Compensation Methods for SINS/CNS Integration

Jia Sheng Yang; Yue Gang Wang

doi:10.4028/www.scientific.net/AMM.390.490

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 390Initial Alignment Error and Navigation Error...

Initial Alignment Error and Navigation Error Compensation Methods for SINS/CNS Integration

Abstract:

To remove the navigation error accumulated in the boost phase of the missile’s SINS/CNS integration system, an error compensation algorithm is presented, which uses the saved IMU data and reverse attitude updating algorithm to remove the error caused by initial misalignments, and uses the off-line navigation computation to correct the boost phase error. The theory analysis show that the proposed algorithm’s performance is mainly dependent on the CNS precision , while the errors caused by gyro and accelerometer drift are tiny., the simulation results show that the proposed algorithm can reduce the velocity error to 0.012m/s and the position error to 1.12 meter, which leads to the navigation error compensated greatly.

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Periodical:

Applied Mechanics and Materials (Volume 390)

Pages:

490-494

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.390.490

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Online since:

August 2013

Authors:

Jia Sheng Yang, Yue Gang Wang

Keywords:

Alignment, Celestial Navigation System (CNS), Error Compensation, Integrated Navigation System, Strapdown Inertial Navigation (SINS)

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