FIELD: spacecraft technologies.
SUBSTANCE: invention relates to ballistic schemes for manoeuvring spacecraft (SC) in low-Earth orbit and can be used to change the phase position of a spacecraft in a given orbital plane. The proposed method includes the formation of a phasing circular orbit (PCO) by issuing a pair of consecutive pulses (with the same change in inclination) after half a revolution, further flight along the PCO to compensate for the required phase angle, and returning to a working circular orbit also by issuing a similar pair of pulses after half a revolution. An orbit is used as a PCO that is synchronous with respect to the regression of the longitude of the ascending node with the working orbit, which is achieved by creating the required mismatch in inclination and height when issuing the first pair of pulses and further compensating it when returning to the working orbit when issuing the second pair of pulses.
EFFECT: absence of restrictions on the achievable phase angles when rephasing the spacecraft, as well as a reduction in the duration of this operation when flying to significant phase angles.
4 cl, 2 dwg, 2 tbl
