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Mechanism of Burning Rate Enhancement by Ferric Oxide
E. W. Price,J. K. Sambamurthi +1 more
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In this article, the mechanism of burning rate enhancement of propellants by catalysts is examined by tests on ammonium perchlorate (AP) sandwiches and bimodal AP propellants.Abstract:
: The mechanism of burning rate enhancement of propellants by catalysts is examined by tests on ammonium perchlorate (AP) sandwiches and bimodal AP propellants Burning rates were measured from motion pictures, and samples from quench tests were examined in the scanning electron microscope The results indicated that effective catalysis depends on concentration of the catalyst on the binder surface so as to permit adequate permitting the oxidizer-fuel flame to stand closer to the surfaceread more
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Journal ArticleDOI
Mechanism of Burning Rate Enhancement of Composite Solid Propellants by Ferric Oxide
TL;DR: In this article, a series of experimental studies performed on sandwich propellants are presented, where a matrix lamina of particulate oxidizer and polymeric binder is sandwiched between two ammonium perchlorate (AP) laminae.
Journal ArticleDOI
The Details of Combustion of Ammonium Perchlorate Propellants: Leading Edge Flame Detachment
TL;DR: In this article, the transition from particle flamelet burning to premixed flame burning of ammonium perchlorate (AP)/hydrocarbon (HC) binder propellants is identified with detachment of the oxidizer/fuel (O/F) flamelet from the stoichiometric tip of the diffusion field over the AP particle.
Journal ArticleDOI
An alternative approach to improve burning rate characteristics and processing parameters of composite propellant
TL;DR: In this article, the effect of IRO content and its specific surface area on burn rate characteristics of composite solid propellant has been investigated and it was observed that IRO is a good burn rate enhancer.
Catalytic Nanoparticle Additives in the Combustion of AP/HTPB Composite Solid Propellant
TL;DR: In this article, the effects of nano-sized particles used as a catalytic additive in composite solid propellant were investigated using various synthesis methods and tested in composite propellant consisting of 80% ammonium perchlorate and 80% hydroxyl terminated polybutadiene.
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Thermal Decomposition Behaviors and Burning Characteristics of Composite Propellants Prepared Using Combined Ammonium Perchlorate/Ammonium Nitrate Particles
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