We assess the possibility of reducing the travel time of a crewed mission to Mars by examining four different propulsion methods and keeping the mass at departure under 2500 t, for a fixed architecture. We evaluated representative systems of three different state of the art technologies (chemical, nuclear thermal and electric) and one advance technology, the “Pure Electro-Magnetic Thrust” (PEMT) concept (proposed by Rubbia). A mission architecture mostly based on the Design Reference Architecture 5.0 is assumed in order to estimate the mass budget, that influences the performance of the propulsion system. Pareto curves of the duration of the mission and time of flight versus mass of mission are drawn. We conclude that the ion engine technology, combined with the classical chemical engine, yields the shortest mission times for this architecture with the lowest mass and that chemical propulsion alone is the best to minimise travel time. The results obtained using the PEMT suggest that it could be a more suitable solution for farther destinations than Mars.
Comparison of Four Space Propulsion Methods for Reducing Transfer Times of Crewed Mars Missions
J Astronaut Sci
The Journal of the Astronautical Sciences ; 69 , 2 ; 284-311
2022-04-01
28 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Crewed Mission , Mars , Chemical Propulsion , Nuclear Propulsion , Electric Propulsion , Electro-Magnetic Propulsion Engineering , Aerospace Technology and Astronautics , Mathematical Applications in the Physical Sciences , Space Sciences (including Extraterrestrial Physics, Space Exploration and Astronautics)
A Value Proposition Analysis of Propulsion Options for Crewed Mars Missions
British Library Conference Proceedings | 2010
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