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Fast computation of high eccentricity orbits by the stroboscopic method

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Abstract

In order to compute with a reasonable accuracy satellite orbits subjected to perturbations byJ 2, the Sun, the Moon and airdrag, a first order expansion is used. The Lagrange equations are solved semi-analytically by the stroboscopic method. The intermediate-, long-periodic and secular terms are obtained, but if desired the same formulism also produces the short-periodic terms. The method is well suited for use on a computer and requires only about 1% of the computing time needed for numerical integration.

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References

  • Bryant, R. W.: 1961,Astron. J. 66, 430.

    Google Scholar 

  • Chebotarev, G. A.: 1967,Analytical and Numerical Methods in Celestial Mechanics, Elsevier, New York.

    Google Scholar 

  • Fitzpatrick, Ph. M.: 1970,Principles of Celestial Mechanics, Acad. Press, New York.

    Google Scholar 

  • Geyling, F. T. and Westerman, H. R.: 1971,Orbital Mechanics, Addison-Wesley, Reading, Mass.

    Google Scholar 

  • King-Hele, D. G.: 1962,Proc. Roy. Soc. London,A267, 541–557.

    Google Scholar 

  • King-Hele, D. G.: 1964,Theory of Satellite Orbits in an Atmosphere, Butterworths, London.

    Google Scholar 

  • Roth, E. A.: 1968, ‘Luni-solar Perturbations of a Highly Eccentric Orbit Satellite’, ESRO, SR-9, Paris.

    Google Scholar 

  • Roth, E. A.: 1971, ‘The Short-Periodic luni-solar Perturbations of the Motion of a Highly Eccentric Orbit Satellite’, ESRO SR-18, Paris.

  • Roth, E. A.: 1972a, ‘The Short-Periodic Perturbations of the Motion of a Test Body in the Field of General Relativity’, ESRO SR-17, Paris.

  • Roth, E. A.: 1972b, ‘Perturbation of a Test Body by a Massive Ring in a Newtonian Field’, ESRO, SR-21, Paris.

    Google Scholar 

  • Roth, E. A.: 1973, ‘Perturbation of a Planetary Orbiter by Radiation Pressure Taking into Account the Variability of the Distance and the Direction of the Sun’, ESRO, SR-24, Paris.

    Google Scholar 

  • Roth, E. A.: ‘Perturbation of an Orbiter by an Oblate Third Body’ (in preparation).

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Authors and Affiliations

  1. Spacecraft Trajectory Division, European Space Operations Center, Darmstadt, FRG

    E. A. Roth

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  1. E. A. Roth
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Roth, E.A. Fast computation of high eccentricity orbits by the stroboscopic method. Celestial Mechanics 8, 245–249 (1973). https://doi.org/10.1007/BF01231423

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  • DOI: https://doi.org/10.1007/BF01231423

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