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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    Title :

    Performance of solid propellants containing metal additives


    Additional title:

    AIAA J


    Contributors:
    Cheung, H. (author) / Cohen, N.S. (author)

    Published in:

    AIAA Journal ; 3 , n 2


    Publication date :

    1965


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :




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