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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    Titel :

    Rocket Thrust Chamber


    Beteiligte:
    E. F. Baehr (Autor:in)

    Erscheinungsdatum :

    1965


    Format / Umfang :

    1 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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