Eclipses intervals for satellites in elliptical orbit under effects of solar radiation pressure and earth’s oblatness

Authors

Ismail M. N., Departments of Astronomy and Metrology* Faculty of Science, Al-Azhar University, Egypt
Bakry A., Departments of Astronomy and Metrology* Faculty of Science, Al-Azhar University, Egypt
Se lim H. H., National Research Institute of Astronomy and Geophysics (NRIAG)
Shehata M. H., National Research Institute of Astronomy and Geophysics (NRIAG)

Corresponding Author

M. N., Ismail

Document Type

Original Article

Subject Areas

Mathematics, Statistics, Computer Science, Physics and Astronomy

Keywords

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

Abstract

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.

How to Cite This Article

M. N., Ismail; A., Bakry; H. H., Se lim; and M. H., Shehata (2015) "Eclipses intervals for satellites in elliptical orbit under effects of solar radiation pressure and earth’s oblatness," Al-Azhar Bulletin of Science: Vol. 26: Iss. 1, Article 12.
DOI: https://doi.org/10.21608/absb.2015.22633