The Effect of Oxidizer Particle Size Distribution on the Steady and Nonsteady Combustion of Composite Propellants.

Abstract

A theoretical analysis of the combustion of composite propellants (with an emphasis on the heterogeneous effects) is presented. The analysis based on the combination of a unique statistical treatment of the burning surface with a very comprehensive multiple flame type of physiochemical model for the combustion process. The analysis is divided into four parts: the steady state burning rate, erosive burning rate, the pressure coupled response, and the velocity coupled response.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1978
Accession Number
ADA056892

Entities

People

  • J .r. Osborn
  • J. A. Condon

Organizations

  • Purdue University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Burning Rate
  • Chemical Kinetics
  • Chemical Reaction Properties
  • Chemical Reactions
  • Combustion
  • Composite Propellants
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Heat Transfer
  • Materials Laboratories
  • Materials Testing
  • Mechanical Properties
  • Propellants
  • Rocket Engines
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Rocket Propulsion.