Accession Number:

AD0395697

Title:

Foamed Aluminum Propellant Study.

Descriptive Note:

Technical rept. Nov 67-Jul 68,

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDSAFB CA

Personal Author(s):

Report Date:

1968-12-01

Pagination or Media Count:

33.0

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 accelerationhigh 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

Subject Categories:

  • Combustion and Ignition
  • Solid Propellant Rocket Engines
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE