A Review of Acceleration Effect of Rocket on The Combustion Mechanism of Composite Solid Propellant

The formulation of the composite propellant is constituted of solid particles of (ammonium perchlorate) as well as metal fuel such as aluminum particles which are all dispersed homogenously within the Binder matrix. The availability of these solid particles affects the combustion mechanism of the composite propellant and causes the betterment in the performance parameters of rocket such as: increasing in specific impulse and burning time. The very accentuation of this paper is upon the acceleration effect and the derived phenomena of its (including agglomeration, pit formation by means of solid particles within propellant matrix, heat feedback, heat transferring -made of agglomerates- unto the surface of propellant which is being burnt) on the combustion mechanism of composite solid fuels which is conducive to increase in the burning rate of propellant. The rest of the paper is devoted to effects of miscellanies of factors such as pressure, static burning rate, and Al content upon increasing the burning rate of propellant.