Document Type : Scientific extension


1 Associate Professor, Department of Chemical Engineering, Faculty of Engineering, Imam Hossein University, Tehran, Iran

2 M. Sc. Student, Department of Chemical Engineering, Faculty of Engineering, Imam Hossein University, Tehran, Iran


The burning rate plays animportant role in determining the performanceandballistic behavior of solid rocket propellant. In this paper, the effect of various factorson burning rate, such as combustion chamber pressure, poropellant grain initial temperature, fuel/oxidizer ratio, composition of the components propellant, oxidizer particle size, motor rocket size, and grain size have been investigated.For this purpose, technologies, methods, and various laboratory equipment are used, the most important of which are the methods such as Crawford, Closed Vessel, Ultrasound Measurement, Microwave, X-Ray X-ray, Plasma Electrical Capacity Measurement, Optical Techniques, Audio Publishing Systems. All of these methods are used in leading countries to measurethe propellants burning rate.Consequently, the appropriate method andequipmentconsidering general aspects (operational, economic, functional, safety, etc.) can be selected, comparing the advantages and disadvantages of each above-mentioned technologies, equipment and methods forthedetermination ofthe burning rate of solid propellants.


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