Parametric Study of Propellant Crack Combustion

Abstract

Selective calculations have been made for burning in cracks as it pertains to solid rocket motor propellants. The possibility of obtaining pressures high enough to cause a shock-to-detonation transition (sdt) in propellant grains is examined. variables affecting the crack combustion process which were selected for study are: crack shape; location; surface roughness; propellant deformation; ignition criterion; and burning rate. The variables are evaluated and ordered in groups of relative importance. results suggest that SDT should not occur in propellants unless the granulation of the grain is severe enough to provide large burning surface area.

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Document Details

Document Type
Technical Report
Publication Date
Oct 21, 1981
Accession Number
ADA108769

Entities

People

  • Kibong Kim

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Burning Rate
  • Chemical Reaction Properties
  • Chemical Reactions
  • Combustion
  • Energetic Materials
  • Erosive Burning
  • Fires
  • Geometry
  • Heat Transfer
  • High Energy Propellants
  • Ignition
  • Mechanical Properties
  • Physical Properties
  • Propellants
  • Rocket Engines
  • Solid Propellants
  • Surface Roughness

Fields of Study

  • Physics

Readers

  • Materials Science (Mechanical Engineering).
  • Rocket Propulsion.
  • Systems Analysis and Design