Accession Number : ADD012740

Title :   Burning Rate Enhancement of Solid Propellants by Means of Metal/Oxidant Agglomerates.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE ARMY WASHINGTON DC

Personal Author(s) : Sayles,David C

Report Date : 07 Apr 1987

Pagination or Media Count : 4

Abstract : Preformed metal/oxidant agglomerates for enhancement of propellant burning rate are prepared from a finely divided metal (aluminum, boron, titanium, etc.), ammonium perchlorate, and a small quantity of the same binder material that goes into the manufacture of the propellant, such as, hydroxyl-terminated polybutadiene crosslinked with a polyisocyanate. Additional ingredients can be incorporated into the agglomerates to bring about further enhancement of burning rate, such as, an ammonium perchlorate decomposition accelerator triphenylbismuthine, a carboranyl burning rate enhancer, iron oxide, etc. Agglomerates are prepared in a fluorinated and/or chlorinated hydrocarbon solvent in which the agglomerate formulation ingredients are insoluble. Any remaining solvent is then evaporated under reduced pressure and the agglomerates are subsequently cured. Optimum mesh size of the agglomerates is 300-500 micrometers. These agglomerates cause major increase in the burning rate of solid propellants when incorporated therein in percentages of 1-5%.

Descriptors :   *PATENTS, *BURNING RATE, *AMMONIUM PERCHLORATE, *SOLID PROPELLANTS, AGGLOMERATES, FORMULATIONS, ALUMINUM, PARTICLE ACCELERATORS, BORON, OPTIMIZATION, IRON OXIDES, BINDERS, MATERIALS, CHLORINATED HYDROCARBONS, SOLVENTS, HYDROXYL RADICALS, POLYBUTADIENE, OXIDIZERS, MESH, SIZES(DIMENSIONS), PROPELLANTS, MATERIAL FORMING, PRESSURE, REDUCTION, TITANIUM

Subject Categories : Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE