Abstract:
Composite propellant properties are directly affected by many processing parameters, particle
size of aluminum is one of these parameters. It affects both mechnical properties and
performance parameters of propellants. This research is mainly foucused on the experimental
study of the effect of using different particle sizes of aluminum on density, tensile strengh,
elongation, burning rate, burning time, average pressure, average thrust, specific impulse, and
thrust coefficient of a typical rocket propellant. This was achieved by using the same weight
percent of ingredients in the propellant and changing only the particle size of aluminum. In
addition, different computer programs were used to determine the probable effect of changing
particle size of aluminum on the propellant properties.