Experimental Studies on the Oscillatory Combustion of Solid Propellants

Abstract

This report describes the results of testing a series of composite and double-base propellants in a T-burner facility. The investigation reveals the unstable combustion behavior that is susceptible of excitation under acoustic pressure-coupled conditions. The degree of instability is quantitatively described in terms of the response function, which is a well- defined characteristic of the propellant. The effect of pressure and frequency has been systematically investigated for the frequency range of 500-10,000 cps and for pressures up to nearly 3,000 psia. Such an extended coverage has permitted the determination of a very general pattern of behavior, including the maximum instability conditions, the isoresponse function contours, and the neutral boundary separating the unstable and stable combustion regimes in the 1. 5-inch T-burner.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1969
Accession Number
AD0853475

Entities

Organizations

  • Naval Air Weapons Station China Lake

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Acoustic Admittance
  • Acoustic Properties
  • Acoustics
  • Ammonium Perchlorate
  • Burning Rate
  • Combustion
  • Combustion Products
  • Combustors
  • Composite Materials
  • Composite Propellants
  • Data Acquisition
  • Double Base Propellants
  • Materials Laboratories
  • Measurement
  • Particle Size
  • Solid Propellants
  • Standing Waves

Fields of Study

  • Physics

Readers

  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.
  • Rocket Propulsion.