Corresponding Author

M. N., Ismail

Document Type

Original Article

Subject Areas

Mathematics, Statistics, Computer Science, Physics and Astronomy


Perturbations Theory; Circular orbital motion; Earth’s gravity; Radiation pressure effects; Shadow function


The eclipse of a satellite in elliptical orbit is studied. The geocentric angle in the orbital plane between the perigee and conjunction point is determined. Eclipse times and duration of eclipse for elliptical orbits are obtained. The effects of the direct solar radiation pressure on the orbital elements are calculated taken into account the eclipses intervals. An application on the MOLNIYA 1-87 artificial satellite is done.

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