One effective method of increasing composite propellant burning rate is by addition of numerous short, nonreactive, metal fibers to basic propellant; analytical studies were directed at thermal processes that occur as single short fibers oriented normal to propellant surface are consumed; characteristics of model were determined by perturbation of important variables about those for 0.8×5×125 mil aluminum fiber in high base rate propellant (1.5 ips); trends predicted agree with those observed experimentally showing that intrinsic ability for burning rate enhancement depends upon thermal diffusivity and melting temperature.


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    Title :

    Influence of embedded metal fibers on solid-propellant burning rate


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Caveny, L.H. (author) / Glick, R.L. (author)

    Published in:

    Publication date :

    1967


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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