Abstract
DAS (Dive and Ascent Satellite) is a kind of satellite that can approach very close to the earth, which was designed by NAL (National Aerospace Laboratory of Japan) in later 1970’s. Now we paid attention to the function of the satellite that can descend and ascend, and proposed to use it for getting detailed information of the area which is suffered from a natural disaster. In this paper orbital control of DAS with minimum fuel consumption is discussed, where the earth is treated as an ellipsoid of revolution, the atmosphere drag and the second zonal coefficient is considered. The optimal orbital control problems are treated as nonlinear two point boundary problems, and solved by the steepest ascent method. The derivation of equations and results are shown in detail.
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