Space Flight of Geostationary Satellite to the Earth with Lunar Gravity Assist
The study deals with a problem of the spacecraft SC re-entry from Geostationary Equatorial Orbit GEO to the Earth. Analysis performed has shown that using the lunar gravity assist allows realization of the “detour” low-energy trajectories for the GEO-Earth re-entry with passive decreasing the perigee radius of the SC orbit. Due to this, one can do this re-entry essentially better from energy point of view, with the smaller fuel consumption than for the usual “direct” flight. For its realization, of course, this scheme requires the larger duration of the flight and more exact navigation and control systems as compared with the “direct” descent to the Earth. The Study is presented on the International Astronautical Forum dedicated to the 20th Anniversary of the School of Astronautics of the Harbin Institute for Technology.