Computer Science
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.701a&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Computer Science
Scientific paper
The transfer from Earth to Mars has been extensively reviewed for a wide range of possible missions and scenarios: GTO passenger, direct launch, Trans Mars Insertion (TMI) from LEO parking orbit, in-orbit assembly, direct entry in Mars atmosphere, aerocapture insertion into a Mars parking orbit or classical propelled braking burn at Mars orbit insertion. All these scenarios are mixed with the use of several propulsion technologies: of-the-shelf storable and cryogenic propellant propulsion but also advanced nuclear propulsion. The comparison between the different options is performed according to the mass of the payload delivered on Mars ground for entry missions (which is considerably less than the overall landing mass of the vehicle) and the mass at beginning of life (MBOL) for Mars orbiter missions. Starting with a hypothetic near future European launcher, derived from the existing ARIANE 5 launcher, with the capability of delivering 30 T payload in LEO, a first analysis is restricted to the use of a single launch to Mars. The main preliminary conclusions are: Although much more important than the envisaged payload mass for near future missions, these figures are far lower than those required for a Mars manned mission where habitation modules or launch ascent vehicle mass budgets could exceed 10 T. Different possibilities are envisaged to cope with such payload mass target.
Augros P.
Bonnefond Francine
Clar Ph.
Jacquelard C.
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