FIELD: transportation.
SUBSTANCE: invention relates to control of transport system during spacecraft (SC) from circumlunar to near-earth orbital station (OS). Proposed method comprises performing spacecraft flight from Moon to Earth along trajectory with span of Earth at preset altitude without aerodynamic umbrella. When this height is reached, a brake pulse is made to transfer the spacecraft to a transient elliptical orbit around the Earth, where the spacecraft is docked with a satellite vehicle carrying an aerodynamic hatch for decelerating the spacecraft in the atmosphere. Besides, satellite vehicle carries fuel of spacecraft refueling for its next flight to near-moon OS. After decoupling from the spacecraft in the apogee of the orbit, the spacecraft performs a braking pulse in order to change over to the orbit at a given height of perigee for braking in the atmosphere by the method of "brake" ellipses. After the apogee of the spacecraft orbit is reduced to the altitude of the orbit of the near-Earth OS, the aerodynamic hood is separated, and in this apogee, the spacecraft is impulsively transferred to the orbit of the OS. After docking with the OS and preventive maintenance, the spacecraft is ready for the next flight to the lunar environment.
EFFECT: reduced duration of flight of spacecraft on "brake" ellipses and reduced volume of preventive works on OS, with possibility of removal of the above spacecraft by means of carrier rocket of middle class.
1 cl, 3 dwg
