Abstract
Using a semi-analytic approach, the effect of oblateness of an artificial satellite on the periodic orbits around the triangular Lagrangian points of the Earth–Moon system is studied. The primaries in this system move in elliptic orbits about their common barycenter, hence we have an elliptic restricted three-body problem. The frequencies of the long and short orbits of the periodic motion are affected by the oblateness of the primaries (Earth and Moon) and of the third body (artificial satellite); and so are their eccentricities, semi-major and semi-minor axes.
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