Author(s): M.R. Amin
In this paper the combined effects of the perturbation due to secular oblateness up to third order and drag force on the semi-major axis and the eccentricity of LEO – satellites are considered. The p urpose of the work is to decrease the resultant perturbation on these parameters. Numerical results are obtained for some critical orbits where these perturbations work against each other. Key words: Oblateness, Air drag, Low Earth orbit satellites.