The patent application relates to 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 therein 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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    Title :

    Improved Rocket Nozzle System


    Contributors:

    Publication date :

    1977


    Size :

    13 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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