Fifth john v. breakwell memorial lecture the restricted three-body problem revisited

摘要

The circular and elliptic restricted three-body problems modelizes respectively 95/100 and 99.9/100 of the lunar motion perturbations. They are also usually the main orbital problem of natural and artificial satellites and space probes. A simple decomposition allows to separate the secular and long period effects from the short Period effects. The perturbations remain small if the inclination is small, but they become very large if the Initial orbit is polar or near polar.