Equations useful in design studies are derived for determining optimum weight distribution for 2-stage tandem rockets for case of different structural factors and propellant specific impulses in each stage; minimization of gross weight for given required burn-out velocity and payload is criterion of optimization used; example included.


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    Titel :

    On optimization of two-stage rockets


    Weitere Titelangaben:

    Jet Propulsion


    Beteiligte:
    Goldsmith, M. (Autor:in)

    Erschienen in:

    Jet Propulsion ; 27 , n 4


    Erscheinungsdatum :

    1957


    Format / Umfang :

    2 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




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