Foamed Aluminum Propellant Study.

Abstract

This report summarizes the results of an AFRPL feasibility study on the use of a new experimental material, foam aluminum. The chief areas of interest center around the value of this material in high-burn-rate, pulse or end-burning motors and high acceleration/high 'Q' loaded antimissile applications. The addition of the foam aluminum to solid propellants made a significant increase in the burning rates of all formulations tested in this limited program. The burning rates of composite modified double-base (CMDB) propellants were increased two to three times their normal burning rates. No change was made in the control formulations other than the substitution of foam aluminum for an equal weight of the aluminum powder. Problems of processing (e. g., loading the propellant into the foam structure, etc.) were studied and found to be resolvable. The mechanical properties of the samples tested indicate superior strain capabilities over previous reinforced propellant systems. It was concluded that foam aluminum is a promising material for solid propellant applications and should be investigated further in laboratory evaluation. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1968
Accession Number
AD0395697

Entities

People

  • B. R. Warren
  • C. G. Bacon

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Ammonium Perchlorate
  • Burning Rate
  • California
  • Combustion
  • Composite Materials
  • Composite Propellants
  • Government Procurement
  • Materials Laboratories
  • Mechanical Properties
  • Propellants
  • Rocket Propulsion
  • Security
  • Solid Propellants
  • Standards
  • Synthetic Rubber
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Polymer Science and Engineering.
  • Rocket Propulsion.