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The low-eccentricity earth satellite orbit at the critical inclination

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Abstract

A solution to the orbital motion of an Earth satellite at the critical inclination and with near-zero eccentricity is developed by the von Zeipel method to the first order in the eccentricity, and to the first order in the higher gravitational harmonics, using elements which do not degenerate at zero eccentricity.

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References

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  • Lyddane, R. H.: 1963,Astron. J. 68, 555–558.

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  • Oesterwinter, C.: 1977, private communication.

  • Raymond, F. W.: 1976, private communication.

  • Sherrill, T. J.: 1976, private communication.

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Authors and Affiliations

  1. Ebeling Associates, 1 Glen Ave., 12302, Scotia, N.Y., USA

    R. H. Lyddane

  2. Naval Surface Weapons Center, 22448, Dahlgren, Va., USA

    Charles J. Cohen

Authors
  1. R. H. Lyddane
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  2. Charles J. Cohen
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Lyddane, R.H., Cohen, C.J. The low-eccentricity earth satellite orbit at the critical inclination. Celestial Mechanics 18, 233–236 (1978). https://doi.org/10.1007/BF01230163

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  • DOI: https://doi.org/10.1007/BF01230163

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