Design issues for lunar ascent and lunar descent rocket engines fueled by aluminum/oxygen propellant produced in situ at the lunar surface were evaluated. Key issues are discussed which impact the design of these rockets: aluminum combustion, throat erosion, and thrust chamber cooling. Four engine concepts are presented, and the impact of combustion performance, throat erosion and thrust chamber cooling on overall engine design are discussed. The advantages and disadvantages of each engine concept are presented.


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    Title :

    Design issues for lunar in situ aluminum/oxygen propellant rocket engines


    Contributors:

    Publication date :

    1992-02-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English







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