Abstract
An orbit transfer system that transports a payload from LEO to GEO using spinning-momentum-tether is introduced in this paper. This system is analyzed in consideration of the change of the angular velocity before and after the catch or the release of the payload for the various parameters of the tether system. The time and the propellant mass required for reboosting the stage are also calculated in detail. As the new thruster for reboosting, the electrodynamic tether (ED tether) system is considered in this study and this system is compared with the conventional ion-thruster system. In addition, the total system mass is optimized for the mission interval that the next transportation of a payload is possible. The results also show that ED tether system can reduce the total system mass compared with ion-thruster system for the same orbit transfer mission.
