Classification of Artificial Earth Satellite Orbital Orientation Systems

  • E. N. Tokar’
  • V. N. Branets
Conference paper

Abstract

The general problem of space vehicle orientation implies the alignment of the like axes of some coordinate trihedron Oxyz associated with the vehicle and a given trihedron Ox0y0z0.* Breaking down the various types of orientation according to the properties of the absolute motion of the trihedron Ox0y0z0, we distinguish the very important class of orientation problems from the practical point of view, when the trihedron Ox0y0z0 executes motion in absolute space with a fixed-orientation nonzero angular velocity vector. The present article discusses some of the problems concerning the sensitive elements (sensors) for orientation that can be used to solve the given type of problem.

Keywords

Torque Assure 

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Literature Cited

  1. 1.
    E. N. Tokar’, Certain Properties of the Gyrocompass with a 17-Hour Period, Prikladnaya Matematika i Mekhanika, Vo. XXV, No. 3, 1961.Google Scholar
  2. 2.
    W. T. Thomson, Stability of Single Axis Gyros on a Circular Orbit, AIAA Journal, Vol. I, No. 7, July, 1963.Google Scholar
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    H. L. Taylor, Satellite Orientation by Inertial Techniques, Journal of the Aerospace Sciences, Vol. 28, No. 6, 1961.Google Scholar
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    C. T. Leondés and R. E. Roberson, Analysis and Synthesis of Satellite Attitude Control Systems, Journal of the Aerospace Sciences, Vol. 29, No. 12, Dec. 1962.Google Scholar

Copyright information

© Springer Science+Business Media New York 1966

Authors and Affiliations

  • E. N. Tokar’
  • V. N. Branets

There are no affiliations available

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