A Simulation Study of the Combustion Mechanism of Aluminum in Solid Rocket Propellant at High Temperatures and Pressures in a Shock Tube

Abstract

The study of aluminum combustion in pure oxygen and mixture (N2-H2- Cl2-O2) at high temperatures and pressures provides a simulation of combustion mechanism study of aluminum powder in solid rocket propellant. Computations were performed for predicting possible intermediate species and products. Emission spectra of important intermediate species were identified by using a spectrometer. Time histories of the AlO emission band show the continuum radiation of Al2O2 in the reaction scheme. The solid and liquid products were observed and analyzed by electron diffraction, X ray diffraction, transmission and scanning electron microscopes. The gaseous products were detected by using infrared spectrometry. These measurements are in good agreement with the computations and provide useful chemical kinetic data. Keywords: Mathematical prediction, Aluminized propellants, Aluminum oxides. (Chinese translations).

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Document Details

Document Type
Technical Report
Publication Date
Sep 10, 1986
Accession Number
ADA172569

Entities

People

  • Zichao Liu

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aluminum Oxides
  • Barometric Pressure
  • Chemical Reaction Properties
  • Chemical Reactions
  • Combustion
  • Combustion Products
  • Diffraction
  • Electron Microscopes
  • High Temperature
  • Propellants
  • Rocket Propellants
  • Shock Tubes
  • Shock Waves
  • Solid Rocket Propellants
  • Spectra
  • X Rays
  • X-Ray Diffraction

Fields of Study

  • Physics

Readers

  • Materials Science and Engineering.
  • Molecular Photonics/Laser Physics
  • ballistics.

Technology Areas

  • Microelectronics