Accession Number:

ADD012742

Title:

A Processing Method for Increasing Propellant Burning Rate.

Descriptive Note:

Patent,

Corporate Author:

DEPARTMENT OF THE ARMY WASHINGTON DC

Personal Author(s):

Report Date:

1987-04-07

Pagination or Media Count:

3.0

Abstract:

The effectiveness of the burning rate accelerator, iron oxide Fe2O3, is enhanced, and a markedly improvement in the mechanical properties of a propellant composition are simultaneously achieved as a result of grinding a composite propellant paste in a roller mill instead of in a conventional sigma blade propellant mixer. The propellant paste is composed of a hydroxyl-terminated polybutadiene prepolymer, fluid-energy mill-ground ammonium perchlorate, dioctyl adipate, aluminum oxide, isophthaloyl bis-1-2-methylaziridine, and iron oxide. The final product has a higher stress capability, higher strain capability, higher modulus, and higher gel fraction, and a burning rate that is about 80 higher as compared with sigma blade propellant ground and mixed propellant.

Subject Categories:

  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE