Advantage of analytical method is fast processing and the physical character of variations of the six orbital elements that due to various perturbations are clearly. So it also has important practical significance in the satellite orbits design, constellation design and orbital stability research. This paper introduces an analytical method of orbit improvement of artificial satellite. After constringency, the root-mean square error is approximately and more than 80% data are used. It means that the fitting result of orbital determination and observational data is good. In the perturbation calculation, the perturbation form long and long periodical terms of J2, J3 and J4 due to non-spherical Earth of gravity field, the short term of J2, as well as long terms of atmospheric drag, solar radiation pressure and lunisolar effects are considered. The arithmetic of differential orbit improvement is used in the corrected estimation of initial elements.
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