Combustion of Aluminum Particles near the Burning Surface in AP/AN Composite Propellants

Citations Over TimeTop 17% of 2015 papers

Abstract

Abstract Aluminum (Al) particles are commonly used in ammonium perchlorate (AP) composite propellants of solid rockets for increasing performance. When propellants including Al particles burn, Al particles easily agglomerate on the burning surface of the propellant. The diameters of agglomerated Al particles are greater than those of mixed particles. The combustion efficiency of the propellant decreases with increasing burning time of the agglomerated Al particles. Therefore, it is important to observe how the agglomerated Al particles burn on the burning surface of AP composite propellant. A lot of researchers have studied Al agglomerate characteristics. Previous studies clarified the relation between the agglomerated Al particle diameter and luminous flame diameter around Al particles near the burning surface. The shapes of luminous flames around agglomerated Al particles are spherical or elliptical. This study evaluates the shapes of the luminous flame around agglomerated Al particles at a constant diameter or a different diameter. When the proportion of the luminous flame diameter ( D f ) to the diameter of agglomerated Al particles ( D 0 ) is 1.54–1.71 at a constant D 0 , the luminous flames are almost perfectly spherical. Otherwise, the luminous flames are elliptical at a constant D 0 . Furthermore, when D f / D 0 is close to the mean value, the luminous flame is more spherical than elliptical at different D 0 . The evaporation rate and the burning rate of Al vapor are inversely proportional to D 0 . The oxidation gas temperatures were changed and the activation energy of Al vapor was obtained as 39.2 kJ mol −1 .

Related Papers

• → Dependence of density and burning rate of composite solid propellant on mixer size(2013)33 cited
• → Modeling of Layered Ammonium Perchlorate Composite Propellant with Different Burning Rates(2021)4 cited
• THE STUDY OF BURNING CHARACTERISTICS OF AP/HTPB/AL BASIC COMPONENTS OF A COMPOSITE PROPELLANT(2011)
• → Combustion Characteristics of Fuel-Rich Solid Propellants(2004)1 cited
• → A Study of Basic Aluminized Propellants Characteristics(2011)