A single metric for judging between two candidate propellant combinations for a given application is sought. By using the ideal rocket equation, the essential link between propellant density and specific impulse as the two primary performance drivers can be demonstrated.


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    Title :

    Rho-Isp Revisited and Basic Stage Mass Estimating for Launch Vehicle Conceptual Sizing Studies


    Contributors:

    Publication date :

    2015


    Size :

    7 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English