Third-body perturbation in the case of elliptic orbits for the disturbing body. (English) Zbl 1151.70011

Summary: This work presents a semi-analytical and numerical study of the perturbation caused in a spacecraft by a third body using a double averaged analytical model with the disturbing function expanded in Legendre polynomials up to the second order. The important reason for this procedure is to eliminate terms due to the short periodic motion of the spacecraft and to show smooth curves for the evolution of the mean orbital elements for a long-time period. The aim of this study is to calculate the effect of lunar perturbations on the orbits of spacecrafts that are traveling around the Earth. An analysis of the stability of near-circular orbits is made, and a study to know under which conditions this orbit remains near circular completes this analysis. A study of the equatorial orbits is also performed.


70M20 Orbital mechanics
70F07 Three-body problems
Full Text: DOI EuDML


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