Projectile

• US 3,890,902 A
• Filed: 12/04/1973
• Issued: 06/24/1975
• Est. Priority Date: 12/04/1973
• Status: Expired due to Term

• Current Assignee: Bruce W. Travor, Samuel L. Brown
• Original Assignee: Bruce W. Travor, Samuel L. Brown
• Inventors: Travor, Bruce W., Brown, Samuel L.
• Primary Examiner(s): Stahl, Robert F.
• Application Number:
  US05/421,570
• Time in Patent Office: 567 Days
• Field of Search: 102/93,92.1,92.2,92.4,92.6,52
• US Class Current: 102/526
• CPC Class Codes: F42B 12/06 with hard or heavy core; Kinetic energy penetrators F42B12/16, F42B12/74 take precedence
• CPC Class Codes: F42B 14/064 Sabots enclosing the rear end of a kinetic energy projectile, i.e. having a closed disk shaped obturator base and petals extending forward from said base

Abstract

A projectile having a pair of longitudinally spaced rotating bands, one of which is forwardly adjacent the projectile center of gravity to provide a projectile bearing surface that minimizes projectile yaw within and at the exit of the gun barrel. An improved aerodynamic stability of the projectile at the gun muzzle exit is obtained, as well as increased projectile accuracy at the target.

Claims

1. In an aerodynamically stable projectile having a heavy penetrator positioned within a non-discarding sabot, said non-discarding sabot including a sabot body portion and an aerodynamic windshield nose member threadedly secured thereto, said heavy penetrator secured within said sabot body portion and said nose member, said nose member having a forward tapered external surface, said nose tapered surface terminating in a closed forward end, said sabot body portion having a forward exterior surface containing a cylindrical portion and a tapered portion forwardly thereof defining an origin of ogive therebetween, said tapered sabot portion being a mating continuation of said nose tapered surface, said sabot body portion carrying a first rotating band rearward of the center of gravity of said projectile, and a second rotating band having a mid-point located on said sabot body portion forward of said projectile center of gravity.

2. The structure in accordance with claim 1 wherein the ratio of maximum surface diameters of said second and first rotating bands is in the range of 0.965 to 0.985.

3. The structure of claim 2 wherein said ratio is 0.975.