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http://dx.doi.org/10.5140/JASS.2014.31.3.199

Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit  

Rahoma, W.A (Department of Astronomy, Faculty of Science, Cairo University)
Publication Information
Journal of Astronomy and Space Sciences / v.31, no.3, 2014 , pp. 199-204 More about this Journal
Abstract
This paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the second order using Legendre polynomials. A double-averaged analytical model is exploited to produce the evolutions of mean orbital elements as smooth curves.
Keywords
Third-body perturbations; averaged model; long period perturbations;
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