Composite Propellant combustion and Transition to Detonation.

Abstract

The steady-state combustion model developed in FY 1979 was further improved by the incorporation of models of aluminum agglomeration and energetic binder combustion. Application of the model to a large variety of composite propellants was successful for the most part. Remaining deficiencies in the model are discussed. Experiments with a porous burner apparatus designed to simulate the diffusion flames of bimodal propellants revealed that fine oxidizer ports tend to operate more fuel-rich than coarse oxidizer ports, and revealed some flame features that are not contained in current propellant combustion models. The potential of the apparatus for more detailed future work is discussed. A literature review of combustion response models that attempt to account for the heterogeneity of composite propellants was completed, and a new response function model based upon a preferred frequency concept was formulated. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1981
Accession Number
ADA102412

Entities

People

  • L. D. Strand
  • N. S. Cohen

Organizations

  • Jet Propulsion Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Burning Rate
  • Combustion
  • Composite Propellants
  • Engineers
  • Flow Rate
  • Governments
  • High Pressure
  • Hydroxyl Terminated Polybutadiene
  • Jet Propulsion
  • Materials Laboratories
  • Particle Size
  • Propellants
  • Rocket Propulsion
  • Solid Propellants
  • Steady State
  • United States Government

Readers

  • Computational Fluid Dynamics (CFD)
  • Rocket Propulsion.