MODEL FOR THE BURNING RATE AND EXTINCTION OF ALUMINIZED POLYBUTADIENE AMMONIUM PERCHLORATE COMPOSITE PROPELLANTS

Abstract

A combustion model and burning rate equation for an aluminized polybutadiene ammonium perchlorate composite solid propellant was developed in terms of the rate of heat feedback to the propellant surface. The equation was used to calculate the propellant extinction behavior in test chambers with low (or subsonic) exhaust flow, and the C* extinction in test chambers exhausting with supersonic flow (i.e. rocket motors). These calculations agreed well with the observed extinction characteristics of the propellant.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1969
Accession Number
AD0706033

Entities

People

  • E. D. Guth
  • G. Schlesinger
  • J. S. Land

Organizations

  • TRW Inc.

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Ammonium Perchlorate
  • Boiling Point
  • Burning Rate
  • California
  • Chemical Properties
  • Chemical Reactions
  • Combustion
  • Composite Propellants
  • Equations
  • Exothermic Reactions
  • Heat Transfer
  • High Pressure
  • Partial Pressure
  • Propellants
  • Solid Propellants
  • Temperature Gradients
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.
  • Rocket Propulsion.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow