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)
Evaluation of Rocket Nozzle Passive Temperature Indicators (Test Nozzle No. 2)
1969
60 pages
Report
Keine Angabe
Englisch
Laboratory & Test Facility Design & Operation , Rocket Engines & Motors , Solid propellant rocket engines , Rocket nozzles , Temperature sensitive elements , Refractory metals , Captive tests , Test facilities , Rocket propellant grains , Nozzle throats , Nozzle area ratio , Flames , Temperature , Erosive burning , Char motors , Evaluation , Uncured propellants
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