The Study of the Mechanism of Enhanced Burning Rate of Solid Propellants

Abstract

In this paper, the problem of burning-rate enhancement of solid propellants by incorporating metallic wires into the propellant matrix is treated by utilizing heat-transfer theory and geometry. It was found that heat conduction considerations incorporating the moving-heat-source restriction to the Fourier equation would adequately describe the process of "coning" and that the geometrical considerations of the coned surface together with the P-K-r data for the matrix propellant would give excellent predictions of the burning rate enhancement. The effects of wire length, wire concentration, and increased burning-rate pressure exponents due to the addition of wire are discussed. Experimental and theoretical P-r plots are presented for a typical staple-containing composite double-base propellant.

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Document Details

Document Type
Technical Report
Publication Date
Mar 20, 1964
Accession Number
AD0348263

Entities

People

  • Lewis J. Hurt

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Burning Rate
  • Combustion
  • Differential Equations
  • Equations
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Mathematical Analysis
  • National Security
  • Physical Properties
  • Propellants
  • Solid Propellants
  • Steady State
  • Surface Temperature
  • Temperature Gradients
  • Thermal Diffusivity
  • United States

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Rocket Propulsion.