Effects of propellant rocket motor aluminum content, chamber pressure, nozzle exit diameter, and lift-off acceleration were evaluated with respect to degradation of protective coatings applied to flame deflectors and umbilical masts; most promising materials were evaluated during scale-model firings; data and scaling factors were correlated with full-scale effects data compiled from launch histories of Titan IIIC; it was found that deflector erosion was not proportional to aluminum content of propellant, and that erosion was influenced by manner in which aluminum affected burning characteristics of propellant.


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    Title :

    Effects of exhausts from aluminized solid propellants on launch facilities


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Lays, E.J. (author) / Darrow, E.A. (author)

    Published in:

    Publication date :

    1967


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :




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