Composite Propellants with Bi-Plateau Burning Behaviour

Abstract

The literature describing the mechanism of combustion in composite rocket propellants exhibiting hi-plateau burning has been reviewed. A wide distribution of AP particle size in a definite coarse/fine ratio is required to ensure adequate interstitial spacing resulting in abnormally depressed burning due to interference of the fine AP fraction combustion by the binder melt layer. Titanium dioxide added to the formulation acts to increase the binder melt layer viscosity restoring normal burning at low and high pressures, leaving abnormal burning and a plateau or mesa effect at intermediate pressures. The use of dimeryl-diisocyanate curative produces a unique plateau at lower pressures due to increased binder liquefaction. Formulation variables can be adjusted to tailor the pressure levels and burn rates of the plateaus formed.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 2002
Accession Number
ADA414445

Entities

People

  • Kym M. Ide

Organizations

  • Defence Science and Technology Group

Tags

DTIC Thesaurus Topics

  • Burning Rate
  • Combustion
  • Composite Materials
  • Composite Propellants
  • High Pressure
  • Materials Laboratories
  • Mechanical Properties
  • Metals
  • Particle Size
  • Particles
  • Propellants
  • Rocket Engines
  • Rocket Propellants
  • Solid Propellants
  • Systems Science
  • Titanium
  • Titanium Dioxide

Readers

  • Mathematics or Statistics
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster