PERTURBED GROUND TRACK UNDER THE INFLUENCE OF J2 AND LUNISOLAR FORCES | ||||
| Al-Azhar Bulletin of Science | ||||
| Article 6, Volume 30, Issue 1-B, June 2019, Page 54-61 PDF (530.08 K) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/absb.2019.66072 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
M. E. Awad1; I. A. Hassan  2; H. R. Dewdar1; A. A. Saad3
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| 1Faculty of Science , Cairo University, Egypt | ||||
| 2Faculty of Science, A l - Azhar University, Cairo, Egypt | ||||
| 3National Authority for Remote Sensing and Space Science, Cairo, Egypt | ||||
| Abstract | ||||
| A several types of forces are acting on the satellite. These forces are classified into conservative and nonconservative force. The main concern in the present research work is to studding the effect of conservative forces on the satellite orbital motion and represent this effect on satellite ground track. Where the ground tracks are the locus of points formed by the points on the Earth directly below a satellite as it travels in orbit. A mathematical model and a program code is designed using Matlab package to calculate the perturbed ground track under J2 and luni-solar forces. Whereas the J2 and Luni-Solar are a conservative forces, the secular variation is presented only in RAAN and . Otherwise the remaining orbital element is varies periodically. The perturbed ground track is calculated under the effect of J2 and luni-solar forces. The perturbed position vectors for a satellite are converted to its corresponding latitudes and longitudes. The satellite’s position in one revolution is displayed to represent where the satellite at the time desired. | ||||
| Keywords | ||||
| Satellite; oblateness; earth’s gravitational force; luni-Solar force; ground Track | ||||
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