Artificial satellites and the three-body problem - A general case

Details Artificial satellites and the three-body problem - A general case Artificial satellites and the three-body problem - A general case

Dec 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991ap%26ss.186..101d&link_type=abstract

Astrophysics and Space Science (ISSN 0004-640X), vol. 186, no. 1, Dec. 1991, p. 101-108.

Astronomy and Astrophysics

Astrophysics

Astrodynamics, Geopotential, Orbital Mechanics, Three Body Problem, Artificial Satellites, Circular Orbits, Earth Gravitation, Equations Of Motion, Legendre Functions, Satellite Orbits

Scientific paper

Attention is given to the planar problem in which the satellites move along close orbits in a plane which forms an angle, theta, with the equatorial plane of the planet, the oblateness of which exercises a great effect. Differential equations of motion are presented and particular solutions are shown to exist when the centers of masses are at the vertices of a nearly equilateral triangle or are collinear. If the first two terms of the Legendre series, with theta = 0, are taken, the same results as Aksenov (1980) are obtained.

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