Direct injection liquid propellant gun system

摘要: A liquid propellant gun system which operates by the direct injection of a two-component hypergolic propellant, i.e., oxidizer and fuel, into combustion chamber in to rear projectile be propelled. The preferred embodiment is an adaption inventive for use as rapid fire, small caliber, high muzzle velocity aircraft cannon system. As components come contact burn, propelled forwardly through out barrel resultant gases. Unlike prior art, permits significantly higher rate fire projectiles, eliminates need igniter, prevents misfires detonations, materially increases reliability thereof, greatly reduces both weight volume needed house other