Title: Direct injection liquid propellant gun system

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

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Inventors: Seifert, Kerry D. (Oakland, CA, US)
Smiley, Parker C. (Oakland, CA, US)

Application Number: 535339
Filing Date: 1974-12-20
Publication_date: 1976-07-20
Assignee: The United States of America as represented by the Secretary of the Air (Washington, DC)
Primary Class(es): 89/7
Other Classes:
US Patent Ref:

2965000	Dec, 1960	Skinner	89/7.
2981153	Apr, 1961	Wilson et al.	89/7.
2986072	May, 1961	Hudson	89/7.
3138990	Jun, 1964	Jukes et al.	89/7.
3313208	Apr, 1967	Dorsey et al.	89/7.
3800657	Apr, 1974	Broxholm et al.	89/7.

Other Refs:
Primary Examiner: Brown, David H.
Assistant Examiner:
Attorney: Rusz; Joseph E., Tashjian; Arsen