A rocket engine for Mars missions is proposed that could utilize CO2 accumulated from the Martian atmosphere as an oxidizer. For use as possible fuel, various metals, their hydrides, and mixtures with hydrogen compounds are considered. Thermodynamic calculations show that beryllium fuels ensure the most impulse but poor inflammability of Be and high toxicity of its compounds put obstacles to their applications. Analysis of the engine performance for other metals together with the parameters of ignition and combustion show that magnesium seems to be the most promising fuel. Ballistic estimates imply that a hopper with the chemical rocket engine on Mg + CO2 propellant could be readily developed. This vehicle would be able to carry out 2-3 ballistic flights on Mars before the final ascent to orbit.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Magnesium and Carbon Dioxide - A Rocket Propellant for Mars Missions


    Contributors:

    Published in:

    Publication date :

    1993-04-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Magnesium and carbon dioxide - A rocket propellant for Mars missions

    SHAFIROVICH, E. IA. / SHIRIAEV, A. A. / GOLDSHLEGER, U. I. | AIAA | 1993





    Powdered Magnesium-Carbon Dioxide Propulsion Concepts for Mars Missions

    Goroshin, S. / Higgins, A. J. / Lee, J. H. S. et al. | British Library Conference Proceedings | 1999