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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Effects of exhausts from aluminized solid propellants on launch facilities


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Lays, E.J. (Autor:in) / Darrow, E.A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1967


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




    Combustion of Aluminized Solid Propellants

    Brill, Thomas B. / Ren, Wu-Zhen / Yang, Vigor | AIAA | 2000


    Microstructure Effects in Aluminized Solid Rocket Propellants

    DeLuca, L. T. / Galfetti, L. / Colombo, G. et al. | AIAA | 2010