Term refers to liquid propellant engines used in ballistic missiles; basic unit is thrust chamber, in which pressure is maintained, and propulsive thrust produced, by continuous combustion of propellants; calculations show that of available propellant combinations, best performance is obtained with liquid oxygen and kerosene type fuel; thrust chamber heat transfer and combustion inefficiency; injector design; combustion instability and starting and control problems.


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    Titel :

    Performance problems in large rocket engines


    Weitere Titelangaben:

    Roy Aeronautical Soc -- J


    Beteiligte:
    Bragg, S.L. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1960


    Format / Umfang :

    10 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


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