Evolution of the special elliptical orbits of synchronous artificial earth satellites

Details Evolution of the special elliptical orbits of synchronous artificial earth satellites Evolution of the special elliptical orbits of synchronous artificial earth satellites

Jan 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991kosis..29..133v&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 29, Jan.-Feb. 1991, p. 133-144. In Russian.

Astronomy and Astrophysics

Astronomy

Artificial Satellites, Astrodynamics, Earth Orbital Environments, Elliptical Orbits, Orbital Elements, Satellite Orbits, Differential Equations, Hill Method, Linear Equations, Synchronous Satellites

Scientific paper

A class of elliptical orbits of artificial earth satellites is studied. The parameters of these orbits are: period of revolution, 1 day, inclination, 60 deg eccentricity 0.5-0.8, argument of the perigee +/- 90 deg. The dependences of the orbital elements on time are obtained from set of linear differential equations in the vicinity of a special solution of the averaged Hill's problem, taking into account the planetary oblateness. These dependences describe satisfactorily the variation of the orbital elements during 5 years.

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