Introduction to the Restricted Jupiter Orbiter Problem

Details Introduction to the Restricted Jupiter Orbiter Problem Introduction to the Restricted Jupiter Orbiter Problem

Sep 1976

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1976cemec..14..175h&link_type=abstract

Celestial Mechanics, Volume 14, Issue 2, pp.175-200

Physics

1

Scientific paper

We consider a restricted six-body problem, consisting of Jupiter, the four Galilean satellites, and an orbiter. The Galilean satellites' orbits are circular and coplanar; Io, Europa, and Ganymede are in exact resonance; their mean longitudes obey the Laplace relation. We seek periodic orbits which avoid close approaches to any satellite; such orbits are of interest for mission planning. They are approximated as equilibrium points of sets of variational equations associated with time-averaged disturbing functions. Stability of the solutions is also determined. The orbits of greatest interest are: Planar: twice Callisto's period, eccentricity≤0.6 Planar: four times Callisto's period, eccentricity≤0.75 Slightly inclined: twice Callisto's period, eccentricity arbitrary Planar: 4/5 or 5/4 Europa's period.

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