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• Hydrogen
  ...nuclear thermal rockets do not make order of magnitude differences in mass fraction over chemical propulsion on short flights like a mission to [[Mars]] and th
  4 KB (671 words) - 04:02, 21 January 2009
• Mars Direct
  ==[[Mass Allocations for Mars Direct|Mass Figures]]== ...anded article focusing specifically on this information, see the article [[Mass Allocations for Mars Direct]]''
  7 KB (1,088 words) - 00:39, 20 March 2010
• NILFiR
  ...-9 in the reactor absorbing a neutron. This will happen in a fairly small fraction of cases. At the optimal Be:Li ratio for neutron production of 1.68, 22% o ...tops. By my calculations, when the Be:Li ratio (by number of atoms, not by mass) is 2:1, 3.64 neutrons will be produced per fission. However, a certain
  5 KB (805 words) - 10:22, 1 September 2010
• Orbital mechanics
  ...ners how much mass they need to deliver to [[LEO]] in order to get a given mass to Mars. For calculating other trajectories Numeric or algebraic techniques
  2 KB (252 words) - 04:02, 21 January 2009
• Solid core
  ...ets are only about twice as efficient as chemical rockets in terms of mass fraction. Another factor that limits the performance of nuclear powered rockets is:
  2 KB (293 words) - 04:02, 21 January 2009
• Mass Allocations for Mars Direct
  On page 92 and 93 of Zubrin's book, [[The Case For Mars]], he gives specific mass estimates for each component of his proposed [[Mars Direct]] Mission. Thes ! Component !! Mass
  5 KB (641 words) - 11:58, 20 March 2010