Accession Number : AD0861814

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

Descriptive Note : Technical rept.,

Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s) : Ellison, John R. ; Binder, Harold I.

Report Date : SEP 1969

Pagination or Media Count : 60

Abstract : 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)

Descriptors :   (*SOLID PROPELLANT ROCKET ENGINES, ROCKET NOZZLES), (*TEMPERATURE SENSITIVE ELEMENTS, REFRACTORY METALS), (*ROCKET NOZZLES, CAPTIVE TESTS), TEST FACILITIES, ROCKET PROPELLANT GRAINS, NOZZLE THROATS, NOZZLE AREA RATIO, FLAMES, TEMPERATURE, EROSIVE BURNING.

Subject Categories : Test Facilities, Equipment and Methods
      Rocket Engines
      Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE