A 6 in. diameter ablative combustion chamber has been designed for use in evaluation tests on rocket engine components. This combustion chamber was designed for operation at 1000 psia chamber pressure with the propellant combination N2O4 and 50% N2H4 - 50% UDMH at a mixture ratio of 2.1/1. This report presents the design and fabrication of two complete combustion chamber assemblies and two spare combustion chamber liners. (Author)


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    Titel :

    The Design and Manufacture of a 6 Inch Diameter Ablative Combustion Chamber


    Beteiligte:
    W. Q. Walker (Autor:in)

    Erscheinungsdatum :

    1965


    Format / Umfang :

    26 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch