Computer Science – Numerical Analysis
Scientific paper
Feb 1988
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1988rpsct.......14v&link_type=abstract
In its JPRS Report: Science and Technology. USSR: Space p 14-15 (SEE N88-30498 24-88) Transl. into ENGLISH from Kosmicheskiye Is
Computer Science
Numerical Analysis
Artificial Satellites, Lunar Effects, Models, Numerical Analysis, Orbital Mechanics, Eccentricity, Ecliptic, Geocentric Coordinates, Geosynchronous Orbits, Solar Longitude
Scientific paper
A study was made of the main features of orbital evolution of artificial earth satellites (AES) with semimajor axes 100 to 200 thousand kilometers in time intervals of about 10 to 15 years using a numerical analysis method. The greatest difficulty is caused by the rather strong lunar perturbing influence. In the analysis this makes it necessary to use a model of an evolving lunar orbit and in the expansion of the perturbing function to take into account a considerably greater number of terms than in the case of the geostationary AES. Orbits with periods commensurate with a sidereal month are not considered. Slower variables (mean solar longitude, ecliptic longitudes of perigee and ascending node of the lunar orbit), changing the periods of 1.9 and 18.5 years, are retained in the perturbing function. Other slow variables in AES orbits which are taken into account are eccentricity, argument of perigee and longitude of the ascending node. In the averaged problem the semimajor axes of AES orbits are constant values. A geocentric ecliptic coordinate system is used as the main system and the averaged equations are written in canonical form for a second system of Poincare elements. The results are compared with the results of numerical integration of rigorous equations of AES motion with allowance for both lunar and solar perturbations. The ranges of changes of eccentricities and inclinations for initial almost circular AES orbits are determined for a 10-year period.
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