Abstract
The automated control of spacecraft formations in specified relative orbits is a challenging problem that is computationally intensive using traditional methods of numerically integrating trajectories and applying optimal control theory. In this paper, relative orbital elements and artificial potential functions are combined into a methodology that allows full control of the relative orbits of spacecraft formations. This method enables the intuitive design of geometrically complex formations, and allows collision avoidance during the formation establishment. The effectiveness of the control algorithm is illustrated with the numerical simulation of the establishment of various formation geometries.
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