IGNITION AND COMBUSTION OF SOLID PROPELLANTS

Abstract

The response of several selected composite propellants subjected to surface heat fluxes was experimentally studied. The surface propellant samples were subjected to thermal-radiation heat fluxes from 1 to 13.5 cal/sec sq cm and convective heat fluxes from 30 to 100 cal/sec sq cm. Parallel theoretical studies, which were guided by the experimental results, have given a satisfactory explanation of the general character of the ignition process. The scope of this research work has been broadened to include several phases of the combustion of solid propellants.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Sep 30, 1962
Accession Number
AD0419883

Entities

People

  • Alva D. Baer
  • John A. Keller
  • Norman W. Ryan
  • Rex C. Mitchell

Organizations

  • University of Utah

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Acrylic Acid
  • Ammonium Perchlorate
  • Burning Rate
  • Chemical Reactions
  • Combustion
  • Composite Propellants
  • Endothermic Reactions
  • Exothermic Reactions
  • Heat Of Activation
  • Heat Transfer
  • Heat Transfer Coefficients
  • Measurement
  • Solid Propellants
  • Surface Reactions
  • Surface Temperature
  • Thermal Conductivity
  • Thermal Diffusivity

Fields of Study

  • Physics

Readers

  • Rocket Propulsion.
  • Theoretical Analysis.
  • Thermal Physics or Thermal Science.