Evolution of the orbits of resonant objects in the case of the elliptical three-body problem

Details Evolution of the orbits of resonant objects in the case of the elliptical three-body problem Evolution of the orbits of resonant objects in the case of the elliptical three-body problem

May 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991kosis..29..484g&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 29, May-June 1991, p. 484-487. In Russian.

Physics

Asteroids, Orbital Elements, Orbital Resonances (Celestial Mechanics), Three Body Problem, Elliptical Orbits, Natural Satellites, Orbit Calculation, Satellite Orbits

Scientific paper

A plane restricted elliptical limited three-body problem is examined.
The equations derived coincide in form with the solution found by
Greenberg and Franklin (1975). It is proposed that the derived equations
be used to investigate the movement of the Hilda-group asteroids as well
as the Titan-Hyperion system.

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