The Small Satellites Orbit Injection and Orbit Transfer Capabilities Using the Vega "Electric Propulsion Service Module "
Abstract
After a short description of the background that originated the decision to design an Orbit Transfer Module to be utilised with the Vega launcher, the main objectives and requirements of such a module are defined. The need to utilise the Electric Propulsion is explained, and the resulting constraints on the missions are addressed (namely the control of transfer time and total dose). The design characteristics of the so called "Electric Propulsion Service Module" (EPSM) as resulting after the completion of the Study phase under ESA contract, is then summarised. The core part of the paper is constituted by the presentation of the mission approaches (firing strategy and attitude control to optimise power availability to the electric Thrusters) and the obtained results (propellant consumption and total transfer time) of the analyses performed for the following missions: LEO to final circular GEO; LEO to Galileo, and Earth to Mars, the last included as example of escape mission. Finally recurring cost considerations and technology spin-off potentials are presented in order to assess the attractiveness of the EPSM service with respect to the alternatives based on GTO.
- Publication:
-
4S Symposium Small Satellites Systems and Services
- Pub Date:
- August 2008
- Bibcode:
- 2008ESASP.660E..12B