DEVELOPMENT OF A TEMPERATURE-INDICATING SENSOR FOR USE IN ABLATIVE ROCKET NOZZLES

Abstract

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.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1967
Accession Number
AD0827922

Entities

People

  • D. C. Rousar
  • J. Deacetis

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Sensors

DTIC Thesaurus Topics

  • Ablative Materials
  • Fabrication
  • Heat Transfer
  • Heat Transfer Coefficients
  • Heating
  • Isotherms
  • Material Degradation Processes
  • Materials
  • Materials Laboratories
  • Materials Processing
  • Materials Science
  • Materials Testing
  • Measurement
  • Test And Evaluation
  • Thermal Conductivity
  • Thermal Properties
  • Tungsten

Fields of Study

  • Physics

Readers

  • Coastal Oceanography
  • Reinforced Composite Materials
  • ballistics.