Abstract
Abstract A mechanism for electrostatic discharge (ESD) ignition of composite rocket propellants was developed based on review of recent literature on spark-induced ignition of gaseous fuel/air mixtures, dispersions of liquid fuel droplets in air, and solid energetic materials. Ignition implies substantial amounts of available propellant are consumed subsequently. The role of mechanical properties in facilitating ignition by maintaining subsurface hot spot pressure developed by the discharge and products of reaction was identified. Other analysis demonstrated additional thermophysical, thermochemical, chemical kinetics, and electrical propellant properties important to ESD sensitivity. Properties which facilitate ignition (e.g., low activation energy for ignition delay) and high propellant burn rate (e.g., small median diameter of oxidizer particle size distribution) favor combustion of the energetic material after a discharge, as do those which inhibit heat losses (small propellant thermal diffusivity) an...
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