Ring airfoil glider with augmented stability

• US 8,661,983 B1
• Filed: 07/28/2008
• Issued: 03/04/2014
• Est. Priority Date: 07/26/2007
• Status: Active Grant

• Current Assignee: Scarr Research And Development Co. LLC
• Original Assignee: Kimball Rustin Scarr
• Inventors: Scarr, Kimball Rustin
• Primary Examiner(s): BERGIN, JAMES S
• Application Number:
  US12/181,190
• Time in Patent Office: 2,045 Days
• Field of Search: 102/502, 102/503, 102/512, 102/520, 102/501
• US Class Current: 102/503
• CPC Class Codes: F42B 10/36 Ring-foil projectiles
• CPC Class Codes: F42B 10/38 Range-increasing arrangements F42B10/34, F42B14/06 and F42B15/105 take precedence

Abstract

In one embodiment, a less lethal munition including a ring airfoil projectile. The flight trajectory of the projectile has increased accuracy resulting from the aerodynamic stabilization of the projectile. In some embodiments, the projectile is both aerodynamically stabilized and spin stabilized.

Claims

1. A munition for a weapon having a barrel, comprising:

a ring projectile symmetrical about a centerline and including a wall having a cross-sectional shape of an airfoil, the airfoil having a chord line, the inner surface of the wall defining the boundary of an inner flowpath, the chord line being non-parallel to the centerline;

a support member for positioning said projectile within the weapon, and

an explosive charge for propelling said projectile;

wherein combustion of said charge propels said projectile out the barrel of the weapon.

2. The munition of claim 1 wherein the chord line is angled relative to the centerline such that rotation of the chord line about the centerline defines a conical surface having a vertex point aft of the trailing edge of the projectile.

3. The munition of claim 1 wherein the explosive charge is adapted and configured to launch the projectile at a subsonic velocity.

4. The munition of claim 1 which further comprises a retainer for retaining said projectile on said support member, a sabot for supporting said projectile on said support member, and a primer for igniting said explosive charge.

5. The munition of claim 1 wherein the airfoil has a mean camber line and the mean camber line is located inward of the chord line.

6. The munition of claim 1 wherein said projectile has a center of gravity, said projectile has an aerodynamic center of pressure, and the center of pressure is behind the center of gravity.

7. The munition of claim 1 wherein the projectile has an outer diameter greater than about 35 mm.

8. The munition of claim 1 wherein the projectile has a leading edge and a trailing edge with a distance therebetween of more than about 20 mm.

9. The munition of claim 1 wherein the explosive charge is adapted and configured to launch said projectile from the barrel with a velocity greater than about 50 m/s.

10. The munition of claim 1 wherein the projectile has a mass of more than about 5 grams.

11. The munition of claim 1 wherein the inner flowpath is substantially unobstructed.

12. The munition of claim 1 wherein the gun is an M203 grenade launcher.

13. The munition of claim 1 wherein the gun is a revolver.

14. The munition of claim 1 wherein the projectile has a length from a leading edge to a trailing edge and a maximum outer diameter, and the ratio of the length to the diameter is greater than about 0.44 and less than about 1.

15. The munition of claim 14 wherein the gun is a Mk19 machine gun.

16. The munition of claim 1 wherein the inner surface smoothly and continuously curves from a leading edge to a trailing edge.

17. The munition of claim 1 wherein the airfoil is asymmetric about the chord line.

18. The munition of claim 1 wherein the airfoil is symmetric about the chord line.

19. A munition for a weapon having a barrel, comprising:

a ring projectile symmetrical about a centerline and including a wall having a cross-sectional shape of an airfoil with a leading edge and a trailing edge, the airfoil having a chord line, the inner surface of the wall defining the boundary of an inner flowpath, the chord line being angled relative to the centerline such that the chord line defines an intersection point with the centerline that is aft of the trailing edge;

a support member for positioning said projectile within the weapon, and

an explosive charge for propelling said projectile;

wherein combustion of said charge propels said projectile out the barrel of the weapon.

20. The munition of claim 19 which further comprises a retainer for retaining said projectile on said support member, a sabot for supporting said projectile on said support member, and a primer for igniting said explosive charge.

21. The munition of claim 19 wherein said projectile has a leading edge and a trailing edge with a distance therebetween of more than about 20 mm, the explosive charge is adapted and configured to launch said projectile from the barrel with a velocity greater than about 50 m/s, and said projectile has a mass of more than about 5 grams.

22. The munition of claim 21 wherein the airfoil is asymmetric about the chord line.

23. The munition of claim 19 wherein the inner flowpath is substantially unobstructed.

24. The munition of claim 19 wherein the gun is a revolver.

25. The munition of claim 19 wherein said projectile has a length from a leading edge to a trailing edge and a maximum outer diameter, and the ratio of the length to the diameter is greater than about 0.44 and less than about 1.

26. The munition of claim 19 wherein the explosive charge propels said projectile at a subsonic velocity.

27. The munition of claim 19 wherein the inner flow path has a minimum diameter, and the minimum diameter is located between the leading edge and the trailing edge.

28. The munition of claim 19 wherein the airfoil is symmetric about the chord line.

29. The munition of claim 19 wherein the projectile has an outer diameter greater than about 35 mm and less than about 45 mm.

30. The munition of claim 19 wherein the airfoil has a mean camber line and the mean camber line is located inward of the chord line.

31. The munition of claim 19 wherein said projectile has a center of gravity, said projectile has an aerodynamic center of pressure, and the center of pressure is behind the center of gravity.

32. The munition of claim 19 wherein the airfoil is asymmetric about the chord line.