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Observability of Star Tracker / Gyro Based Attitude Estimation Considering Time-Variant Sensor Misalignment

  • Stefan Winkler

Abstract

The fusion of measurements from star trackers and gyroscopes within optimal estimators/filters is a common approach for spacecraft attitude determination. For applications where filter tuning is not sufficient to account for unmodelled deterministic errors, state augmentation is often the method of choice. So also here, where the focus is on deterministic time-variant misalignment between star tracker and gyroscope unit as this often occurs in missions with repetitive ecplipse and sun phases. Based on the derived filter dynamics and measurement equations, an observability analysis is performed. Different practical cases are distinguished to analyze: (1) which filter states are observable, (2) which only in linear combination and (3) which not at all.

Keywords

Attitude Estimation Inertial Measurement Unit Spacecraft Attitude Star Tracker State Augmentation 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. 1.
    Crassidis, J.L., Junkins, J.L.: Optimal Estimation of Dynamic Systems. Chapman & Hall/CRC, Boca Raton (2004)zbMATHCrossRefGoogle Scholar
  2. 2.
    Crassidis, J.L., Markley, F.L., Cheng, Y.: Survey of Nonlinear Attitude Estimation Methods. Journal of Guidance, Control and Dynamics 30(1), 12–28 (2007)CrossRefGoogle Scholar
  3. 3.
    Iwata, T., Hoshino, H., Yoshizawa, T., Kawahara, T.: Precision Attitude Determination for the Advanced Land Observing Satellite (ALOS): Design, Verification, and On-Orbit Calibration. In: AIAA Guidance, Navigation and Control Conference, Hilton Head, SC, August 20-23 (2007), AIAA-2007-6817Google Scholar
  4. 4.
    Kalman, R.E.: On the General Theory of Control Systems. In: Proceedings IFAC Moscow Congress, vol. 1, pp. 481–492. Butterworth Inc., Washington DC (1960)Google Scholar
  5. 5.
    Lefferts, E., Markley, F., Shuster, M.: Kalman Filtering for Spacecraft Attitude Estimation. Journal of Guidance, Control and Dynamics 5(5), 417–429 (1982)CrossRefGoogle Scholar
  6. 6.
    Markley, F.L.: Attitude Error Representations for Kalman Filtering. Journal of Guidance, Control and Dynamics 26(2), 311–317 (2003)MathSciNetCrossRefGoogle Scholar
  7. 7.
    Minkler, G., Minkler, J.: Theory and Application of Kalman Filtering. Magellan Book Company (1993)Google Scholar
  8. 8.
    Shuster, M.D.: A Survey of Attitude Representations. Journal of the Astronautical Sciences 41(4), 439–517 (1993)MathSciNetGoogle Scholar
  9. 9.
    Winkler, S., Wiedermann, G., Gockel, W.: Gyro-Stellar Attitude Estimation Considering Measurement Noise Correlation and Time-Variant Relative Sensor Misalignment. In: International Astronautical Congress, Glasgow, Scotland, September 29 - October 3 (2008), IAC-08-C1.7.4 Google Scholar
  10. 10.
    Winkler, S., Wiedermann, G., Gockel, W.: High-Accuracy On-Board Attitude Estimation for the GMES Sentinel-2 Satellite: Concept, Design, and First Results. In: AIAA Guidance, Navigation and Control Conference, Honolulu, HI, August 18-21 (2008), AIAA-2008-7482Google Scholar
  11. 11.
    Wu, Y.-w.A., Li, R.K., Robertson, A.D.: Precision Attitude Determination for GOES N Satellite. In: 26th Annual AAS Guidance and Control Conference, Breckenridge, CO, February 5-9 (2003), AAS 03-002 Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2011

Authors and Affiliations

  • Stefan Winkler
    • 1
  1. 1.AOCS/GNC and Flight Dynamics, Astrium GmbH - SatellitesFriedrichshafenGermany

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