METHOD OF LAUNCHING SPACECRAFTS INTO GEOSTATIONATY ORBIT USING ELECTRIC PROPULSION ENGINES Russian patent published in 2017 - IPC B64G1/26 F03H1/00 

FIELD: aviation.

SUBSTANCE: method comprises launching spacecraft (SC) into exchange orbit with an apogee altitude of more than the altitude of the geostationary orbit (GSO) and a pericentre altitude below the GSO. The final launching of spacecraft is carried out in two stages, at the first stage the inclination of the exchange orbit is reduced by means of electric propulsion engines of high thrust (e.g., electrothermal ones), providing its natural evolution for the settlement period. Then the pericentre altitude of the exchange orbit is increased, ensuring that the spacecraft misses the inner radiation zone. At the second stage the spacecraft is launched into GSO using electric propulsion engines of low thrust (e.g., ion or plasma ones). Inertial orientation of the spacecraft remains unchanged throughout the second stage. The drift speed of the spacecraft is changed in the desired direction and the final launching is combined by the eccentricity to longitude reduction along with the changes in the eccentricity of the orbit.

EFFECT: reduction in time and resources connected with the preparation for the arming operation and launching spacecraft into orbit of normal operation.

4 cl, 3 dwg