Abstract:
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Knowledge and investigation about low-thrust propulsion systems have been
increasing during the last years and some spacecrafts employing this technology
have succeeded in their objectives, which contribute to the possible selection of
low-thrust technology for future space missions. Missions to Mars, which are
currently being propelled by chemical engines, are subject of study in this field for
future exploration missions to the planet.
This project presents a code that computes a transfer from Earth to Mars using
low-thrust electric propulsion. This code is analysed and later employed to
perform a study of different transfers by varying the parameters of the simulation.
The study includes the analysis of the performance of electrical engines (both
existing or under development) that have been used in the simulations of the
transfer trajectory. The results of the best transfers in terms of minimum flight
time and fuel mass consumed are presented and discussed.
The study shows that the main advantage of selecting low-thrust propulsions
systems are the savings in propellant mass, with the corresponding increase in
the mass of payload that can be delivered to Mars. This makes the mission even
more interesting from the point of view of the scientific objectives, especially
those implying the delivery of equipment to the surface. On the other hand, the
drawback is represented by the higher transfer times, even of some years, than
those implied by the adoption of chemical engines. However, this study also
shows that as the thruster characteristics of the electrical engines increase in
performance, such shortcoming becomes less significant. |