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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    Titel :

    Space carrier vehicles, rocket engines, propellants


    Weitere Titelangaben:

    Traegerraketen, Triebwerke, Treibstoffe


    Beteiligte:
    Scholze, O. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1964


    Format / Umfang :

    11 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Deutsch


    Schlagwörter :


    Rocket propellants

    Engineering Index Backfile | 1960



    SOLID ROCKET PROPELLANTS

    Mama, Horrrluz P. | Online Contents | 1996


    Applicability of solid propellants to high-performance rocket vehicles

    Summerfield, M. / Shafer, J.I. / Thackwell, Jr., H.L. et al. | Engineering Index Backfile | 1962


    Cryogenic rocket propellants.

    Douglass, H. W. | NTRS | 1967