On the effect of the central body small deformations on its satellite trajectory in the problem of the two-body gravitational interaction

Abstract

The problem of the two-body gravitational interaction has been solved numerically based on the classical mechanics principles. One of the bodies is a deformable three-axis ellipsoid (central body) and the other is a material point (satellite). The relationship of the angular discrepancy between the calculated and actual positions of the satellite pericenter with central body's gravity anomaly has been established.