The objective of this test was to demonstrate a technique for measuring subsurface nozzle material temperatures beyond the range of conventional thermocouples. The objective was achieved by designing and fabricating a 2.3-inch-throat-diameter solid rocket nozzle and instrumenting it with high-temperature indicators, the evaluation and selection of propellant ballistic properties to obtain 6500 degrees F flame temperature, 810-psig maximum chamber pressure, 21.9-sec effective firing duration, and posttest evaluation of the rocket nozzle including X-ray analysis and sectioning. (Author)


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    Titel :

    Evaluation of Rocket Nozzle Passive Temperature Indicators (Test Nozzle No. 2)


    Beteiligte:
    J. R. Ellison (Autor:in) / H. I. Binder (Autor:in)

    Erscheinungsdatum :

    1969


    Format / Umfang :

    60 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Rocket nozzle test method Patent

    Estes, E. G. | NTRS | 1970




    Rocket Nozzle System

    H. A. Krayenbuhl / G. Dolgonas / C. J. Rogers | NTIS | 1977


    Analytical evaluation of rocket nozzle ablation

    KENDALL, R. / RINDAL, R. | AIAA | 1964