Accession Number : ADA298066
Title : Gas-Phase Metal Reactions.
Descriptive Note : Final rept. 1 Mar 92-28 Feb 95,
Corporate Author : RENSSELAER POLYTECHNIC INST TROY NY DEPT OF CHEMICAL ENGINEERING
Personal Author(s) : Fontijn, Arthur
PDF Url : ADA298066
Report Date : 24 MAY 1995
Pagination or Media Count : 64
Abstract : The use of new advanced solid rocket propellant constituents, such as, e.g., boron as HEDM and ammonium nitrate as replacement for halogen-containing oxidants, requires knowledge of their combustion characteristics. To this end experimental rate coefficient k measurements on individual important Al and B species reactions were made in the 300-1800 K temperature range using a high- temperature fast-flow reactor. Temperature dependent rate coefficient expressions k(T) = AT(super n)exp(-E/RT) are found for the reactions between AlO and CH4, O2; Al and N2O: AlCl and N2O, CO2, SO 2; BCl and N2O, SO2; BO and CO2. To allow semi-empirical predictions for further metal oxidation reactions, two semi-empirical theories have been developed and utilized. These are Semi-Empirical Configuration Interaction theory for prediction of E from one species to another and metals-Transition State Theory for prediction of k(T) from k at one temperature. Dual military-civilian applications of this work are discussed. jg p. 1
Descriptors : *METALS, *GASES, DENSITY, MILITARY PERSONNEL, PREDICTIONS, INTERACTIONS, MOLECULES, PHASE, HIGH ENERGY, COMBUSTION, ALUMINUM OXIDES, CONFIGURATIONS, CHEMICAL REACTIONS, CHLORIDES, METHANE, NITROGEN OXIDES, CARBON DIOXIDE, BORON, OXIDATION REDUCTION REACTIONS, HALOGENS, SOLID ROCKET PROPELLANTS, SULFUR OXIDES, AMMONIUM NITRATE, REACTIVE GASES.
Subject Categories : Inorganic Chemistry
Atomic and Molecular Physics and Spectroscopy
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE