Wake stabilized supersonic combustion ram cannon

• US 4,726,279 A
• Filed: 11/12/1986
• Issued: 02/23/1988
• Est. Priority Date: 11/12/1986
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Deblois, Raymond L., Spadaccini, Louis J., Kepler, Charles E.
• Primary Examiner(s): BENTLEY, STEPHEN
• Application Number:
  US06/929,533
• Time in Patent Office: 468 Days
• Field of Search: 89/8, 89/7, 60/270.1, 102/501, 102/381, 244/3.1, 244/160
• US Class Current: 89/8
• CPC Class Codes: F41A 1/04 Missile propulsion using the combustion of a liquid, loose powder or gaseous fuel, e.g. hypergolic fuel

Abstract

A supersonic combustion ram cannon (1) includes a conical projectile (8) with a flat base (9) which produces a subsonic wake (12) as it flies through a barrel (2). The projectile is configured to avoid a normal shock, relying instead on supersonic compression, combustion and gas expansion. The supersonic combustion of a fuel-oxidizer mixture around the tail of the subsonic wake, pressurizes the wake and drives the projectile forward. By utilizing wake stabilized supersonic combustion, the compression and combustion pressures can be matched to the limiting barrel working pressure, thereby providing for optimum thrust and maximum projectile acceleration.

Claims

1. A wake stabilized supersonic combustion ram cannon in combination with a projectile, said cannon being of the type adapted for firing said projectile therethrough in accordance with ramjet principles, said cannon including a barrel having a bore extending therethrough, a breech end and a muzzle end, and means for sealing said barrel ends, wherein said projectile traveling through said barrel bore compresses a fuel-oxidizer mixture contained therein, gas generated by the ignition and combustion of said compressed mixture accelerating said projectile through said barrel, said projectile comprising an essentially conically shaped body with an essentially flat base, the projectile and barrel configured to provide supersonic compression and combustion of said fuel-oxidizer mixture, said concically shaped body producing a convergent subsonic wake as it travels through said barrel, said wake stabilizing the supersonic combustion process by spreading the combustion gases over the diverging region surrounding the wake, moderating pressures within the barrel, such that the compression and combustion pressures are essentially matchable to the barrel limiting pressure, thereby maximizing projectile acceleration.

2. The ram cannon of claim 1 wherein said projectile and barrel are configured to provide supersonic compression with an aerodynamic contraction ratio of from 0.05-0.50.

3. The ram cannon of claim 2 wherein said projectile are configured to provide supersonic compression with an aerodynamic contraction area ratio of 0.25.

4. The ram cannon of claim 1 wherein said fuel-oxidizer mixture comprises a mixture of a gaseous fuel and an oxidizer.

5. The ram cannon of claim 1 wherein said projectile has an optimally balanced center of gravity to provide stabilized flight at supersonic speeds.

6. A projectile for use in a ram cannon of the type adapted for firing a projectile therethrough in accordance with ramjet principles, said cannon including a barrel having a bore extending therethrough, a breech end and a muzzle end, and means for sealing said barrel ends, wherein said projectile traveling through said barrel compresses a fuel-oxidizer mixer contained therein, gas generated by the combustion of said compressed mixture accelerating said projectile through said barrel, said projectile comprising:

an essentially conically shaped body with an essentially flat base, configured relative to said barrel for providing supersonic compression and combustion of said fuel-oxidizer mixture, said conically shaped body producing a covergent subsonic wake as it travels through said barrel, said wake stabilizing the supersonic combustion process by spreading the combustion gases over the diverging region surrounding the wake, moderating pressures within the barrel, such that the compression and combustion pressures are essentially matchable to the barrel limiting pressure, thereby maximizing projectile acceleration.

7. The projectile of claim 6 configured, relative to said barrel, for providing supersonic compression, with an aerodynamic contraction ratio of from 0.05-0.50.

8. The projectile of claim 7 configured, relative to said barrel, for providing supersonic compression with an aerodynamic contraction ratio of 0.25.

9. The projectile of claim 6 having an optimally balanced center of gravity to provide stabilized flight at supersonic speeds.