The large area-ratio nozzles are for a lightweight rocket motor thrust chamber construction such as is disclosed in patent No. 2,943,442. The thrust chamber is composed of a combustion chamber, a throat, and a nozzle portion. The nozzle portion is formed of a compound wall having radially spaced inner and outer surfaces formed from a plurality of elongated compound channel members disposed in contiguous side-by-side relation to define an internal annular chamber.


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    Title :

    Rocket Thrust Chamber


    Contributors:
    E. F. Baehr (author)

    Publication date :

    1965


    Size :

    1 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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