A method for low-thrust spiral maneuver design using numerical optimization in a modeling and mission analysis environment is presented. Control solutions are determined using a differential corrector approach with initial guesses based on sets of Thrust-Fourier Coefficients (TFCs). The TFC approach enables low-thrust controls with periodically varying magnitude and direction. Configurations are described for an engine plugin and a thruster set that can implement the TFC-defined continuous controls in the modeling environment. The method is demonstrated on two types of low-thrust spiral maneuvers: a repositioning maneuver in geosynchronous Earth orbit and a maneuver to simultaneously change orbit radius and incli-nation.
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