In-Situ Solid-Propellant Burn-Rate Measurements Using Flash Cineradiography

Abstract

Flash radiography has been applied to the measurement of solid- propellant burn rates during a series of solid-propellant rocket motor tests at AEDC. This technique offers the advantage of realistic operating conditions and higher data rates than other measurement techniques. The propellant grains were cylindrically perforated and had action times ranging from 2.2 to 3 sec. Four of the six motors were designed to exhibit varying degrees of erosive burning. Chamber pressure and axial thrust were measured on each of the tests. Approximately 25 radiographs (at a rate of 6 per second) were recorded during the tests. These radiographs were subjected to three different methods of image processing. In addition to the quantitative data obtained, many interesting burn anomalies were revealed in the radiographs.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1986
Accession Number
ADA167637

Entities

People

  • L. M. Smith
  • R. A. Gamble
  • R. Y. Walker

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Burning Rate
  • Combustion
  • Cross Correlation
  • Data Rate
  • Data Reduction
  • Erosive Burning
  • Image Processing
  • Materials
  • Measurement
  • Propellant Grains
  • Propellants
  • Rocket Engines
  • Solid Propellants
  • Strain Gages
  • Test Facilities
  • X Rays

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Nuclear and Radiation Engineering.
  • Rocket Propulsion.