The patent describes an improved rocket nozzle system having a closure insulator located adjacent the combustion chamber of a rocket engine. The closure insulator has formed as an integral part thereof a plurality of nozzles. Each of the nozzles has incorporated therin a throat insert of pyrolized graphite cloth laminate and a consumable washer. The entire closure insulator assembly including nozzles is transfer molded as one piece into a steel housing. The housing is mounted on the combustion chamber thereby providing an effective nozzle system which is reliably operable under high temperature operation. (Author)


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    Titel :

    Rocket Nozzle System


    Beteiligte:
    H. A. Krayenbuhl (Autor:in) / G. Dolgonas (Autor:in) / C. J. Rogers (Autor:in)

    Erscheinungsdatum :

    1977


    Format / Umfang :

    6 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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