On One Class of Systems for Controlling the Orientation of Artificial Earth Satellites

  • V. A. Bodner
  • K. V. Alekseev
  • G. G. Bebenin
Conference paper

Abstract

Combination systems of control are used for orienting satellites designed for protracted flight times. The best control for satellites travelling in relatively low orbits is provided by control systems in which the load on a flywheel is imposed by a magnetic torquer. Investigation of such systems (1, 2, 3, 7) has explained the most characteristic properties of practical application of such systems, their design, and their construction.

Many problems of design and computation of combination systems with magnetic drives for the case of three-dimensional orientation of satellites, however, require further investigation. The greatest difficulties in such investigations are due to the difficulty of combining the processes of controlling angular motion and loading of flywheels in a general dynamic pattern. Another important problem is synthesis of flywheel systems characterized by control-channel crosstalk.

The present paper is devoted to carrying investigation of these problems to the point required for indicating possible methods for solving them. Since the article is written from the theoretical viewpoint, the satellites under discussion are not assigned concrete purposes. The requirements imposed on the system, however, are quite specific:
  1. 1)

    Minimum mean-square error in satellite orientation;

     
  2. 2)

    Minimum energy consumption for torquing flywheels.

     

The same assumptions as adopted in (3) lie at the base of the investigation.

Keywords

Torque Bital 

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References

  1. (1).
    McElvain, R. J., Satellite Angular Momentum Removal Utilizing the Earth’s Magnetic Field, New York, London Academic Press, 1964.Google Scholar
  2. (2).
    Renuie, R. G., A Magnetic Unloading System for an Ultan Stabbe Unmanned Spacecraft, IEEE Transactions on Aerospace, N2, 1964.Google Scholar
  3. (3).
    Bodner, V. A., Alekseev, K. B., and Bebenin, G. G., On Application of Magnetic Torquers for Three-Dimensional Stabilization of Artificial Earth Satellites, “Inzhernenyi zhrnal, Vol. 4, No. 4, 1964.Google Scholar
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    Stuart, W. H., Satellite Attitude Stabilization by Means of Flywheels, “Aerospace Engineering,” Vol. 20, No. 9, 1961.Google Scholar
  5. (5).
    Alekseev, K. B., and Bebenin, G. G., Toward a Thoery for Synthesis of Stabilization Systems for Artificial Earth Satellites with Flywheels, Trudy MVGU im. Bumana (in press).Google Scholar
  6. (6).
    Alekseev, K. B., and Bebenin, G. G., Control of Cosmic Flight Apparatus, Mashinostroenie, 1954 (in Russian).Google Scholar
  7. (7).
    Bodner, V. A., Alekseev, K. B., and Bebenin, G. G., Use of Magnetic Torquers for Loading Flywheels.Google Scholar
  8. (8).
    Bodner, V. A., The Theory of Automatic Flight Control, Izd. Nauka, 1964 (in Russian).Google Scholar
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    Roitenberg, L. Ya., A Gyroscopic Servosystem for Operation in the Presence of Multidimensional Random Noise, “PMM,” XXVI, 2.Google Scholar
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    Leondes, C. T., Roberson, R. E., Aoxi, M., Analysis and Synthesis of a Particular Class of Satellite Attitude-Control Systems, “Aerospace Science,” Vol. 29, No. 12, 1962.Google Scholar

Copyright information

© Springer Science+Business Media New York 1966

Authors and Affiliations

  • V. A. Bodner
  • K. V. Alekseev
  • G. G. Bebenin

There are no affiliations available

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