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Accurate computation of highly eccentric satellite orbits

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Abstract

For computing highly eccentric (e≳0.9) Earth satellite orbits with special perturbation methods, a comparison is made between different schemes, namely the direct integration of the equations of motion in Cartesian coordinates, changes of the independent variable, use of a time element, stabilization and use of regular elements. A one-step and a multi-step integration are also compared.

It is shown that stabilization and regularization procedures are very helpful for non or smoothly perturbed orbits. In practical cases for space research where all perturbations are considered, these procedures are no longer so efficient. The recommended method in these cases is a multi-step integration of the Cartesian coordinates with a change of the independent variable defining an analytical step size regulation. However, the use of a time element and a stabilization procedure for the equations of motion improves the accuracy, except when a small step size is chosen.

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Authors and Affiliations

  1. European Space Operations Centre, Darmstadt, F.R.G.

    Guy Janin

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  1. Guy Janin
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Janin, G. Accurate computation of highly eccentric satellite orbits. Celestial Mechanics 10, 451–467 (1974). https://doi.org/10.1007/BF01229121

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  • DOI: https://doi.org/10.1007/BF01229121

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