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Influence of Particle Size and Temperature on the Burning Rate of Small Caliber Ball Powder

: The performance of a small-caliber propellant is influenced by many factors. Foremost is the chemical composition, however, other factors such as the physical properties of the propellant, the weapon system, and the operating conditions can also greatly influence the performance of a propellant. In this study, researchers investigated the influence of particle size and temperature on the performance of small caliber, ball powder propellant. Particle size is important as it provides the initial surface area available for a propellant to begin the deflagration process. The geometry of the grain will dictate how the deflagration pro-gresses: progressively, regressively, or neutral. The initial temperature of the propellant also has a direct influence on propellant performance. Evaluations were conducted in a constant volume, a temperature-controlled closed vessel to obtain pressure-time data for the various experiments. The data coupled with the propellant thermochemical properties were used to calculate the burning rate coefficient ( β ) and pressure exponent ( α ) of the propellant. Dynamic vivacity, relative force, and relative quickness values are also re-ported. The performance of a small caliber propellant is influenced by many factors. Foremost is the chemical composition, however, other factors such as the physical properties of the propellant, the weapon system, and the operating conditions can also greatly influence the performance of a propellant. In this study, researchers investigated the influence of particle size and temperature on the performance of small caliber, ball powder propellant. Particle size is important as it provides the initial surface area available for a propellant to begin the deflagration process. The geometry of the grain will dictate the manner in which the deflagration progresses: progressively, regressively, or neutral. The initial temperature of the propellant also has a direct influence on propellant performance. Evaluations were conducted in a constant volume, temperature controlled closed vessel to obtain pressure-time data for the various experiments. The data coupled with the propellant thermochemical properties were used to calculate the burning rate coefficient (β) and pressure exponent (α) of the propellant. Dynamic vivacity, relative force, and relative quickness values are also reported.