Trajectories in the doubly averaged elliptical restricted three-body problem

Details Trajectories in the doubly averaged elliptical restricted three-body problem Trajectories in the doubly averaged elliptical restricted three-body problem

Jun 1979

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1979azh....56..623a&link_type=abstract

Astronomicheskii Zhurnal, vol. 56, May-June 1979, p. 623-631. In Russian.

Astronomy and Astrophysics

Astronomy

4

Celestial Mechanics, Natural Satellites, Three Body Problem, Trajectory Analysis, Eccentric Orbits, Gravitational Effects, Orbital Mechanics, Quadratures

Scientific paper

The satellite version of the doubly averaged elliptical restricted
three-body problem is considered. Equations are obtained which describe
the trajectories in this problem. Special attention is given to
trajectories that lead to collision of the satellite with the central
body.

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