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A Multiplicative Residual Approach To Attitude Kalman Filtering With Unit-Vector Measurements

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Abstract

Using direction vectors of unit length as measurements for attitude estimation in an extended Kalman filter inevitably results in a singular measurement covariance matrix. Singularity of the measurement covariance means no noise is present in one component of the measurement. Unit-vector measurements have no noise in the radial component. Singular measurement covariances can be dealt with by the classic Kalman filter formulation as long as the estimated measurement covariance is non-singular in the same direction. Unit-vector measurements violate this condition because both the true measurement and the estimated measurement have perfectly known lengths. Minimum variance estimation for the unit-vector attitude Kalman filter is studied in this work. An optimal multiplicative residual approach is presented. The proposed approach is compared with the classic additive residual attitude Kalman filter.

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References

  1. Kalman, R.E. “A New Approach to Linear Filtering and Prediction Problems,” Journal of Basic Engineering, Vol. 82, March, 1960, pp. 35–45.

    Article  Google Scholar 

  2. Kalman, R.E. and Bucy, R.S. “New Results in Linear Filtering and Prediction,” Journal of Basic Engineering, Vol. 83, March, 1961, pp. 95–108.

    Article  MathSciNet  Google Scholar 

  3. Kuipers, J.B. Quaternions and Rotation Sequences, Princeton University Press, Princeton, NJ, 1999.

    MATH  Google Scholar 

  4. Markley, F.L. “Attitude Estimation or Quaternion Estimation?” The Journal of the Astronautical Sciences, Vol. 52, January–June, 2004, pp. 221–238.

    MathSciNet  Google Scholar 

  5. Lefferts, E.J., Markley, F.L., and Shuster, M.D. “Kalman Filtering for Spacecraft Attitude Estimation,” Journal of Guidance, Control, and Dynamics, Vol. 5, No. 5, 1982, pp. 417–429.

    Article  Google Scholar 

  6. Bar-Itzhack, I.Y. and Oshman, Y. “Attitude Determination from Vector Observations: Quaternion Estimation,” IEEE Transaction on Aerospace and Electronic Systems, Vol. 21, January, 1985, pp. 128–135.

    Article  Google Scholar 

  7. Simon, D. and Chia, T.L. “Kalman Filtering with State Equality Constraints,” IEEE Transactions on Aerospace and Electronic Systems, Vol. 38, January, 2002, pp. 128–136.

    Article  Google Scholar 

  8. Zanetti, R., Majji, M., Bishop, R.H., and Mortari, D. “No. 5, Norm-Constrained Kalman Filtering,” Journal of Guidance, Control, and Dynamics, Vol. 32, No. 5, 2009, pp. 1458–1465.

    Article  Google Scholar 

  9. Shuster, M.D. “Kalman Filtering of Spacecraft Attitude and the QUEST Model,” The Journal of the Astronautical Sciences, Vol. 38, July–September, 1990, pp. 377–393.

    Google Scholar 

  10. Cheng, Y., Crassidis, J.L., and Markley, F.L. “Attitude Estimation for Large Field-of-View Sensors,” The Journal of the Astronautical Sciences, Vol. 54, July–December, 2006, pp. 433–448.

    Article  Google Scholar 

  11. Mortari, D. and Majji, M. “Multiplicative Measurement Model and Single-Point Attitude Estimation,” Paper AAS 08-263 in the Proceedings of the AAS F. Landis Markley Astronautics Symposium, 2008, Cambridge, MD, pp. 51–69.

    Google Scholar 

  12. Deutschmann, J., Bar-Itzhack, I., and Galal, K. “Quaternion Normalization in Spacecraft Attitude Determination,” AIAA/AAS Astrodynamics Specialist Conference, Hilton Head SC, August 1992.

  13. Markley, F.L. “Attitude Error Representations for Kalman Filtering,” Journal of Guidance, Control, and Dynamics, Vol. 26, No. 2, 2003, pp. 311–317.

    Article  MathSciNet  Google Scholar 

  14. Crassidis, J.L., Andrews, S.F., Markley, F.L. and HA, K. “Contingency Designs for Attitude Determination of TRMM,” NASA/GSFC Flight Mechanics Symposium, NASA/CP 3299, Greenbelt, MD, May 1995.

  15. Akella, M.R., Seo, D., and Zanetti, R. “Attracting Manifolds for Attitude Estimation in Flatland and Otherlands,” The Journal of the Astronautical Sciences, Vol. 54, July–December, 2006, pp. 635–655.

    Article  MathSciNet  Google Scholar 

  16. Reynolds, R.G. “Asymptotically Optimal Attitude Filtering with Guaranteed Convergence,” Journal of Guidance, Control, and Dynamics, Vol. 31, No. 1, 2008, pp. 114–122.

    Article  Google Scholar 

  17. Catlin, D. E. “Estimation, Control, and the Discrete Kalman Filter,” No. 71, Applied Mathematical Sciences, Springer-Verlag, New York, 1989, p. 160.

    Google Scholar 

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Correspondence to Renato Zanetti.

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Zanetti, R. A Multiplicative Residual Approach To Attitude Kalman Filtering With Unit-Vector Measurements. J of Astronaut Sci 57, 793–801 (2009). https://doi.org/10.1007/BF03321530

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