Abstract
The main objective of this paper is to calculate the perturbations of tide effect on LEO's satellites . In order to achieve this goal, the changes in the orbital elements which include the semi major axis (a) eccentricity (e) inclination , right ascension of ascending nodes ( ), and fifth element argument of perigee ( ) must be employed. In the absence of perturbations, these element remain constant. The results show that the effect of tidal perturbation on the orbital elements depends on the inclination of the satellite orbit. The variation in the ratio decreases with increasing the inclination of satellite, while it increases with increasing the time.
Highlights
Perturbations are deviations from a normal, idealized, or unperturbed motion
The results show that the effect of tidal perturbation on the orbital elements depends on the inclination of the satellite orbit
The actual motion will vary from the theoretical two-body path due to perturbations caused by other bodies and additional forces not considered in Keplerian motion
Summary
Perturbations are deviations from a normal, idealized, or unperturbed motion. Tthe most accurate method to analyze perturbations is via numerical analysis. The periodic tidal deformations of the Earth give rise to small but significant perturbations in the motions of close satellites, as pointed out by Kaula (1962). The effects of tidal deformation of earth, due to the sun and the moon, on close earth satellites were discussed by Yoshihide Kozai (1965) These effects are about ten percent of the direct luni-solar gravitational perturbations, and it is found that the eccentricity as well as the semi-major axis are not perturbed by the tides when the short-periodic terms are neglected. The main objective of this paper is to determine the tidal effects on Low Earth Orbits (LEOs) satellites, which are considered in satellite geodesy as mostly circular. The appropriate basic equations that were formulated by Lagrange are the relation between the acting perturbing forces and the time dependent variations of the orbital elements.
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