Comparison of Four Space Propulsion Methods for Reducing Transfer Times of Crewed Mars Mission. (arXiv:1502.06457v3 [physics.pop-ph] UPDATED)
<a href="http://arxiv.org/find/physics/1/au:+Guerra_A/0/1/0/all/0/1">A. G. C. Guerra</a>, <a href="http://arxiv.org/find/physics/1/au:+Bertolami_O/0/1/0/all/0/1">O. Bertolami</a>, <a href="http://arxiv.org/find/physics/1/au:+Gil_P/0/1/0/all/0/1">P. J. S. Gil</a>
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 tonne, 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.
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 tonne, 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.
http://arxiv.org/icons/sfx.gif
