Abstract The problem of optimization of the interplanetary trajectory of flight for a multistage spacecraft with high- and low-thrust engines into the Jupiter satellite orbit is considered. Low-thrust engines (stationary plasma engines) are used on a heliocentric flight segment. Their operation is maintained with electric power supply from solar batteries. The principal feasibility of the realization of such a project is shown, and estimations of the mass of a spacecraft placed into Jupiter's satellite orbit are presented.
The Use of a Solar Electrojet Propulsion System for Jupiter Satellite Injection
Cosmic Research ; 40 , 2
2002
Aufsatz (Zeitschrift)
Englisch
BKL: | 55.60 Raumfahrttechnik / 39.00 Astronomie: Allgemeines / 50.93 Weltraumforschung | |
Lokalklassifikation TIB: | 770/3520/8000 |
The Use of a Solar Electrojet Propulsion System for Jupiter Satellite Injection
Springer Verlag | 2002
|NTRS | 1988
|Development of the Jupiter Propulsion System
British Library Conference Proceedings | 1997
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