Volume 40 Issue 12
Dec.  2014
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Han Li, Zhang Lijun, Cai Hong, et al. A method of stellar-inertial attitude determination under high dynamic condition[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(12): 1767-1772. doi: 10.13700/j.bh.1001-5965.2013.0756(in Chinese)
Citation: Han Li, Zhang Lijun, Cai Hong, et al. A method of stellar-inertial attitude determination under high dynamic condition[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(12): 1767-1772. doi: 10.13700/j.bh.1001-5965.2013.0756(in Chinese)

A method of stellar-inertial attitude determination under high dynamic condition

doi: 10.13700/j.bh.1001-5965.2013.0756
  • Received Date: 10 Jan 2014
  • Publish Date: 20 Dec 2014
  • Under high dynamic condition, the accuracy of stellar-inertial attitude determination degraded or even failed to obtain the attitude information because of star image smearing. Based on multiplicative extended Kalman filter (MEKF), a deep integration attitude determination method using gyro and star sensor was proposed. The attitude estimation errors and gyro drifts were compensated by using the star sensor information. The relationship between the gyro output and the pixel motion of the image was established, then the smearing parameters could be estimated by using the gyro output. The star image was restored by using Wiener filter with estimated smearing parameters to improve the signal-to-noise ratio and observation accuracy. Simulation results show that the estimation accuracy of star centroid and the recognition rate of star image can be improved remarkably, the initial attitude estimation errors can be modified faster. The method eliminates recognition mistakes and ensures high accuracy of attitude determination under high dynamic condition.

     

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