EXTINCTION OF BURNING SOLID PROPELLANT

Abstract

The paper presents the results of a combined theoretical and experimental study of the process in which solid propellant combustion is terminated by a rapid drop in pressure. Experimentally, propellant burning in a small rocket motor was subjected to a rapid pressure drop when an auxiliary nozzle was suddenly opened. Such tests were run with varying nozzle sizes for the auxiliary nozzle and the boundary between extinction and non-extinction was determined. The results were then compared to the predictions of the theoretical model which was based on the assumption that extinction occurs when the heat absorption by the solid propellant surface exceeds the heat transfer to the solid propellant surface from the combustion gas. In general, the theoretical predictions agreed well with both the experimental results gathered in the program and those published by other investigators.

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Document Details

Document Type
Technical Report
Publication Date
May 25, 1967
Accession Number
AD0661971

Entities

People

  • M. D. Horton

Organizations

  • Brigham Young University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Burning Rate
  • Chemical Engineering
  • Combustion
  • Combustion Chambers
  • Engineering
  • Engineers
  • Equations
  • Experimental Data
  • Extinction
  • Heat Energy
  • Heat Transfer
  • Literature
  • Phase
  • Plastic Explosives
  • Rocket Engines
  • Solid Propellants
  • Surface Temperature

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Rocket Propulsion.