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 research aims to show the relationship between these factors and the burning rate in order to evaluate factor that is more effective on burning rate, so to calculate of burning rate as a function of this factor. Accordingly, this could be used to achieve ballistics characteristics required for rocket motor design and performance.
This paper represented a result of several visions of chemical phenomenon and several extractions and extrapolations of experimental works which included a relationship between energy related to a chemical process and the relevant time which is required to achieve this process, but it must be taken into account that those mentioned experimental works hadn’t aimed substantially to study and state this relationship neither implicitly nor explicitly, but the results of those works have been exploited for another field after being compared with the relevant thermodynamic calculations. The selected case study for this paper was the relation between the burning time of Hydroxyl terminated poly butadiene propellant ( HTPB) and the caloric value of this material. The results reflected some relationship between the burning time and the change of the system energy during the burning process.
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