Integration of the elliptic restricted three-body problem with Lie series

Details Integration of the elliptic restricted three-body problem with Lie series Integration of the elliptic restricted three-body problem with Lie series

Dec 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984cemec..34..145d&link_type=abstract

(Bundesministerium für Wissenschaft und Forschung of Austria, Alexander von Humboldt Colloquium on Celestial Mechanics: The Stab

Mathematics

11

Celestial Mechanics, Elliptic Differential Equations, Lie Groups, Series (Mathematics), Three Body Problem, Operators (Mathematics), Orbit Calculation

Scientific paper

The method of Lie series is used to construct a solution for the elliptic restricted three-body problem. In a synodic pulsating coordinate system, the Lie operator for the motion of the third infinitesimal body is derived as function of coordinates, velocities and true anomaly of the primaries. The terms of the Lie series for the solution are then calculated with recurrence formulae which enable a rapid successive calculation of any desired number of terms. This procedure gives a very useful analytical form for the series and allows a quick calculation of the orbit.

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