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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    Title :

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


    Contributors:

    Publication date :

    1969


    Size :

    60 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Rocket nozzle test method Patent

    Estes, E. G. | NTRS | 1970




    Rocket Nozzle System

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


    Rocket nozzle development

    Bunting, D. | Engineering Index Backfile | 1962