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Attitude stability of a symmetric satellite at the equilibrium points in the restricted three-body problem

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Abstract

A problem of attitude motion of the smallest body for the restricted three-body problem is analyzed. Axial symmetry is assumed for the body, and attention is focused on the case in which the symmetry axis is normal to the orbit plane. For libration point satellites, results are similar to those for a satellite in orbit about a single body. However, for orbit equilibrium points lying on the line joining the two larger bodies, attitude stability results depart markedly from those for the two-body problem.

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References

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Authors and Affiliations

  1. Stanford University, Stanford, Calif, U.S.A.

    T. R. Kane

  2. Jet Propulsion Laboratory, Pasadena, Calif, U.S.A.

    E. L. Marsh

Authors
  1. T. R. Kane
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  2. E. L. Marsh
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Additional information

This paper presents the results of one phase of research carried out at the Jet Propulsion Laboratory, California Institute of Technology, under Contract No. NAS 7-100, sponsored by the National Aeronautics and Space Administration.

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Kane, T.R., Marsh, E.L. Attitude stability of a symmetric satellite at the equilibrium points in the restricted three-body problem. Celestial Mechanics 4, 78–90 (1971). https://doi.org/10.1007/BF01230323

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  • DOI: https://doi.org/10.1007/BF01230323

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