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.


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    Title :

    Propellant production from the Martian atmosphere


    Contributors:

    Published in:

    Publication date :

    1992-08-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English