Abstract
The deployment procedure of a constellation is complex and depends on the separation distance between any pair of satellites within the constellation. The deployment procedure can be divided into two stages: the deployment from a circular parking orbit to an elliptical orbit, and the correction of the separation distance between pairs of satellites within the constellation. The solution of this problem is implemented with a combination of Hohmann transfer maneuvers and the digital linear quadratic regulator control scheme showing a minimum consumption of fuel. In summary, the combination of these two techniques provides a different approach to the deployment procedure of a constellation.
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