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On the Oxidation and Combustion of AlH 3 a Potential Fuel for Rocket Propellants and Gas Generators
Author(s) -
Weiser Volker,
Eisenreich Norbert,
Koleczko Andreas,
Roth Evelin
Publication year - 2007
Publication title -
propellants, explosives, pyrotechnics
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.56
H-Index - 65
eISSN - 1521-4087
pISSN - 0721-3115
DOI - 10.1002/prep.200700022
Subject(s) - propellant , arrhenius equation , specific impulse , materials science , combustion , hydrogen , rocket propellant , aluminium , rocket (weapon) , thermodynamics , chemical engineering , chemistry , activation energy , metallurgy , organic chemistry , physics , engineering , aerospace engineering
Abstract Aluminum hydride is a promising candidate for application in energetic materials and hydrogen storages. E.g. an AP/HTPB rocket propellant filled with alane was calculated for a 100 N s kg −1 higher specific impulse compared to the same concentration of aluminum. Different investigations on α‐AlH 3 polyhedra using thermoanalytical methods and X‐ray diffraction were performed to receive a better understanding of dehydration at about 450 K, passivation of the remaining porous aluminum particles and further oxidation. A modeling approach to describe these conversions including diffusion processes, Avrami‐Erofeev mechanism and Arrhenius type reaction steps of n‐th order were introduced. Results were discussed in comparison to experimental investigations under pressure with model propellants on the base of gelled pure nitromethane and also filled with alane or pure aluminum in concentrations of 5%, 10% and 15%. Both alane and aluminum increase the burning rate on a factor of two correlated with a temperature increase up to 500 K and more. A mesa burning effect at 6 to 10 MPa was indicated by the mixtures with alane.