THE SATELLITE MODEL FOR SYSTEM OF THREE BODIES

Abstract

The classical method of the variation of arbitrary constants is applied for the calculation of perturbation of elements of the planet satellite due to the gravitation of the third body. The mutual inclination of the satellite orbit and the disturbing body orbit is arbitrary and eccentricities do not surpass Laplace's limit. Corresponding procedure described by means of ALGOL-60 is applied to Jupiter's X satellite. A comparison of the results with Lemechova's theory based on Delaunay's expansions for the Moon is made.