Evolution of orbits in the restricted circular doubly averaged three-body problem. I - Qualitative study

Details Evolution of orbits in the restricted circular doubly averaged three-body problem. I - Qualitative study Evolution of orbits in the restricted circular doubly averaged three-body problem. I - Qualitative study

Jan 1981

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1981kosis..19....5v&link_type=abstract

Kosmicheskie Issledovaniia, vol. 19, Jan.-Feb. 1981, p. 5-18. In Russian.

Computer Science

Numerical Analysis

2

Orbit Calculation, Orbit Perturbation, Orbital Mechanics, Three Body Problem, Eccentric Orbits, Entire Functions, Numerical Analysis

Scientific paper

A numerical-analytical method is used to compute the secular part of the disturbing function for orbit evolution in the restricted circular doubly averaged three-body problem. It is considered that the large semi-axis of the zero-mass point orbit and the projection of its kinetic moment on the normal to the orbit plane of the disturbing body are parameters of arbitrary value. The structure of the integral curves is found to vary in the plane of these parameters. New stationary solutions are found which correspond to highly eccentric orbits, orthogonal to the orbit plane of the disturbing body.

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