Test firings of rockets were made to study effects of propellant composition, pressure, and engine size on exhaust oxide particle size, and on composition of solid exhaust products; results of work and those by others were analyzed to better understand aluminum combustion and oxide condensation processes in rocket motors; combustion of aluminum was found to occur in vapor phase, and was essentially complete in engines studied although some combustion took place in nozzle; results indicate that condensation of oxide vapor can be described by first-order chemical kinetics; further particle growth by agglomeration appears likely.


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    Titel :

    Performance of solid propellants containing metal additives


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Cheung, H. (Autor:in) / Cohen, N.S. (Autor:in)

    Erschienen in:

    AIAA Journal ; 3 , n 2


    Erscheinungsdatum :

    1965


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




    Solid Propellants Containing Activated Aluminum

    Wingborg, N. / Wanhatalo, M. / Johansson, M. et al. | British Library Conference Proceedings | 2006