| 摘要 |
The invention relates to a combined propulsion system for a spacecraft, combining an electric propulsion system and a tether propulsion system, characterized in that the electric propulsion system is an electrostatic system (EP) which has, on the one hand, a generator (G) for ejecting an ionized plasma, comprising at least one grid for electrostatically accelerating the ions in the plasma and, on the other hand, an electron generator (NM) generating electrons to maintain the electrical neutrality of the system, and in that the electron generator (NM) is coupled to a first end of the tether which is the opposite end to the end at which the plasma-ejection generator (G) is arranged, generating a compensating current (Ic) flowing along said tether.
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