Distributed satellites (DS) moving in low earth orbit is suffered from the influence of atmospheric perturbation , and the orbit configuration of the DS is destroyed soon. The center of the relative orbit of the circling satellite is drifting continuously. This study was conducted to establish a compensatory approach to reduce the influence of atmospheric perturbation on the orbit configuration of the DS. Thus , the orbit configuration can be maintained naturally better. In the study , based on the atmospheric density model considering the effect of altitude change and diurnal variation of solar radiation , the semi- major axis perturbation equation of circling satellite with different initial phase in the DS is deduced. A semi- major axis modified method is presented to compensate the influence of atmospheric perturbation. It is shown from the simulation that the influence of the atmospheric perturbation can be decreased greatly in a given time period using this modified method

Matlab Simuli nk.pdf

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