DEVELOPMENT OF A TEMPERATURE-INDICATING SENSOR FOR USE IN ABLATIVE ROCKET NOZZLES
Phase rept. no. 1, 1 Aug-6 Oct 1967
AEROJET-GENERAL CORP SACRAMENTO CA
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The primary purpose of this program is to develop a high temperature 3500-6000F indicating system in order to obtain internal temperature measurements in ablative type materials during rocket motor firings. During the first phase of work, a state-of-the-art survey was conducted to determine those necessary factors which would permit the accurate measurement of in depth temperatures. A high-temperature indicating system was designed based upon the phase equilibrium of refractory materials in the 3500-6000F range.
- Test Facilities, Equipment and Methods
- Rocket Engines