Transient Combustion Calculations with Variable Thermal Properties

Abstract

The response of solid propellant combustion to steep pressurization pulses has been calculated with consideration of temperature dependent thermal properties of the solid and quasi-steady gas phase. Response has been calculated for a uniformly distributed gas phase reaction and for the Zeldovich heat feedback theory with variations in surface heat release, pressurization rate, and thermal properties of the solid. Regression rate excursions of two to three times the quasi-steady rate are calculated for nominal values of propellent properties. For pressurization rates approximating calculated DDT rates, the excursions survive at high pressure. Higher assumed surface heat release produces sharper response in the distributed flame models. The Zeldovich approach predicts protracted excursions from quasi-steady behavior.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1981
Accession Number
ADA098657

Entities

People

  • Carl W. Nelson

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Burning Rate
  • Chemical Reactions
  • Combustion
  • Composite Propellants
  • Double Base Propellants
  • Engineering
  • Heat Capacity
  • Heat Transfer
  • Materials
  • Measurement
  • Mechanical Engineering
  • Military Research
  • Pressurization
  • Propellants
  • Security
  • Solid Propellants
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

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