Optimization of conditions for transfer to frozen sun-synchronous orbit with repeating ground track using low-thrust engines with restrictions on control

The paper discusses the problem of controlling a satellite with the use of low-thrust engines during its transfer from the injection orbit established by the launch vehicle to the sun-synchronous orbit with stable altitude profile and repeating ground track. It is assumed that duration of each maneuver is limited and the orbital averaged eccentricity vector is forced towards the centre of the circle drawn by the eccentricity vector during its natural passive drift. The optimal parameters (semi-major axis, eccentricity and argument of perigee) of the injection orbit that provide minimum duration of the transfer are determined within the limits of the specified conditions. The track shift and deviation of local time of ascending node accumulated during multiple-turn transfer period are estimated. It is shown that the deviation of local time of ascending node has to be taken into account when calculating right ascension of ascending node of the injection orbit and the track shift has to be removed at the end of transfer to the operational orbit. The achieved results are intended for design estimations of satellite’s orbital parameters, transfer duration and propellant consumption.