FIELD: cosmonautics.
SUBSTANCE: invention relates to rocket and space engineering, namely to methods of launching spacecrafts (SC). To inject spacecraft into the target orbit, the radius of the apocentre of the low reference orbit is determined, which provides sufficient time for the existence of the spacecraft. Guaranteed fuel reserves are calculated for reaching this orbit. Velocity pulses are applied to the spacecraft and the last stage with guaranteed fuel reserves to form a reference orbit. Spacecraft is separated from the stage and pulses are applied to transfer to the target orbit. After separation, actual orbit parameters are measured. If necessary, an additional speed increment is calculated and applied to achieve the target orbit.
EFFECT: higher efficiency of fuel use.
1 cl, 1 dwg, 2 tbl
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