Fundamental relations between characteristic velocity, exhaust gas velocity, number of stages, propellant weight ratio, structural factor, takeoff to payload weight ratio, and thrust ratio, are determined and represented in preliminary design diagrams; summary of various rocket propulsion systems is followed by theory of ideal nozzle and influence parameters determining exhaust velocities in real nozzles; basic equations for evaluating rocket engines are compiled and analyzed. (See also n 25 Sept (I) 1964 p 1227-33)


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    Title :

    Space carrier vehicles, rocket engines, propellants


    Additional title:

    Traegerraketen, Triebwerke, Treibstoffe


    Contributors:
    Scholze, O. (author)

    Published in:

    Publication date :

    1964


    Size :

    11 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    German


    Keywords :


    Rocket propellants

    Engineering Index Backfile | 1960



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