Results are presented from a calculation of the specific impulses that can be generated through the combustion of cryogenic CO and O2 over a range of fuel/oxidizer ratios, chamber pressures, nozzle expansion ratios, freestream pressures representative of Mars, and the limiting conditions of equilibrium and frozen nozzle flow. For an expansion ratio of 80 and 100-atm. chamber pressure, a specific impulse of 298 sec was obtained; this is comparable to the best solid rocket propellants.
Propellant production from the Martian atmosphere
Journal of Propulsion and Power ; 8 , 4, Ju
1992-08-01
Miscellaneous
No indication
English
Propellant production from the Martian atmosphere
AIAA | 1992
|Comment on "Propellant Production from the Martian Atmosphere"
Online Contents | 1993
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