Numerical models for the study of motion of lunar satellites
The author deals with the numerical analysis of the planar (circular and elliptic) restricted three-body problem (RTBP) as well as of the perturbed RTBP by a fourth body (Sun). The power series method, and fifth-order Runge-Kutta method are used. Simple and multiple (up to multiplicity 165) quasiperiodic orbits of lunar satellites of negligible mass (with Earth and Moon as primaries) are calculated, and results are presented in graphical form in the inertial barycentric as well as in the rotating system.
planar (circular and elliptic) restricted three-body problem
scientific article; zbMATH DE number 3907848