Solid Propellant Admittance Measurements by the Driven Tube Method.

Abstract

The progress made during the fourth year of an investigation for the measurement of the response of a burning solid propellant to flow disturbances is presented. In this study a modification of the impedance tube technique is used to measure the response over a wide frequency range. Further refinements in the data reduction computer program are discussed. Anomalous behavior for high pressure (300 psig) tests which shows that the propellant sample periodically drives and damps acoustic oscillations during a burn was resolved. Techniques for improving the accuracy of the measured data and the quality of the burn have been developed. Testing will resume during the next year. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1977
Accession Number
ADA052537

Entities

People

  • B. R. Daniel
  • B. T. Zinn
  • M. Salikuddin
  • W. A. Bell

Organizations

  • Georgia Tech

Tags

Communities of Interest

  • Advanced Electronics
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Acoustic Properties
  • Acoustic Waves
  • Acoustics
  • Air Force
  • Combustion
  • Computer Programs
  • Computers
  • Heat Transfer
  • Materials
  • Nozzles
  • Propulsion Systems
  • Rocket Engines
  • Rocket Propulsion
  • Rockets
  • Standing Waves
  • Temperature Gradients

Fields of Study

  • Physics

Readers

  • Plasma Physics / Magnetohydrodynamics
  • Rocket Propulsion.
  • Systems Analysis and Design