Abstract:Burning rate is one of the most important characteristics of rocket propellants and it is affected by many factors including composition, pressure, initial temperature, oxidizer particles size and burning rate modifier. This research aims to study experimentally the effects of combustion chamber pressure, initial temperature and particles size of the oxidizer material on the burning rate of solid composite propellant. Besides, study theoretically the effect of composition and catalyst used. In addition, this r… Show more
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