Predicted and Measured Effects of Pressure and Crossflow Velocity on Composite Propellant Burning Rate

Abstract

A theoretical model for prediction of burning rates of composite (ammonium perchlorate oxidizer) solid propellants as a function of pressure and crossflow velocity has been developed. Included in this model is the capability for treatment of multimodal oxidizer particle sizes and metalized formulations. In addition, an experimental device for measuring the effects of crossflow velocity on propellant burning rate has been developed and used to characterize a series of AP/HTPB propellants with systematically varied formulation parameters. Model predictions of zero-crossflow burning rate versus pressure characteristics have been found to be in excellent agreement with data, while the agreement between erosive burning predictions and data is in general good.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1980
Accession Number
ADA098090

Entities

People

  • Merrill K. King

Organizations

  • ARCO

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Burning Rate
  • Combustion
  • Composite Propellants
  • Cross Flow
  • Erosive Burning
  • Layers
  • Measurement
  • Particle Size
  • Skin Friction
  • Solid Propellants
  • Thermal Conductivity
  • Transport Properties
  • Two Dimensional
  • United States

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Rocket Propulsion.