An analysis of space trajectories characteristics for the Earth-Apophis-Earth mission
UDC
521.1+629.78EDN
YMTQRWAbstract
The spacecraft trajectories for the Earth-Apophis-Earth space expedition with the flight to asteroid Apophis, staying there for some time and the following return to the Earth are studied in the paper. Optimal trajectories (with maximum useful mass) and their characteristics for the flights during 2019-2022 years using the existing high thrust engines, with the total flight duration up to two years, are determined and investigated. It is shown that there is principal possibility of implementing the Earth-Apophis -Earth space expedition based on the launch vehicles "Soyuz-FG", "Soyuz-2", "Zenit" and the upper stage "Fregat". The SC motion around the asteroid is investigated for the main SC and for a mini-satellite with radio-device taking into account three perturbations: the gravitational effects of far celestial bodies (Sun, Earth, Moon, Venus, and Jupiter), non-spherical structure of Apophis and solar radiation pressure. It was shown that it is possible to choose such orbits of the main SC and the mini-probe that their motions will be stable for long enough time. In particular, it is possible to have stable motion of the mini-probe during about several years (for instance, from 2020 till approach to the Earth in 2029).
Keywords:
asteroid Apophis, space mission Earth-Apophis-Earth, high thrust engines, optimal space trajectories, orbital motion, Apophis artificial satellite, solar radiation pressure, asteroid's nonsphericity, lifetime of satelliteReferences
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