Ring airfoil glider with augmented stability

• US 9,404,721 B2
• Filed: 02/28/2014
• Issued: 08/02/2016
• 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:
  US14/193,855
• Publication Number:
  US 20140245918A1
• Time in Patent Office: 886 Days
• Field of Search: 102/501, 102/502, 102/503, 102/439, 102/520, 102/517, 89/11, 89/11.1
• US Class Current: 1/1
• 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 method for launching a ring airfoil projectile from a weapon, comprising:

providing a ring-shaped projectile having an outer diameter, the wall of the projectile having the cross-sectional shape of an airfoil, the projectile having a center of gravity, the projectile having an aerodynamic center of pressure;

explosively propelling the projectile within the weapon;

spinning the projectile as it travels within the weapon; and

aerodynamically stabilizing the projectile by placing the center of pressure behind the center of gravity.

2. The method of claim 1 wherein the airfoil shape has a smooth trailing edge, and which further comprises modifying the aft end of the projectile to increase the aerodynamic drag from the trailing edge.

3. The method of claim 1 wherein the projectile has a centerline, the airfoil has a chord line, and said placing is by providing an angle of attack of the chord line relative to the centerline.

4. The method of claim 1 wherein the airfoil has a chord line and a mean camber line, the chord line and the camber line being non-coincident, and said placing is having the central portion of the camber line inward to the chord line.

5. The method of claim 1 wherein said explosively propelling is by at least one of combustion of an explosive charge or release of compressed gas.

6. The method of claim 1 wherein the weapon includes a chamber that is rifled, and said spinning is by interaction between the projectile and the rifling.

7. The method of claim 1 wherein the projectile is adapted and configured to be less-lethal, and 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 diameter is greater than about 0.44 and less than about 1.

8. The method of claim 1 wherein the projectile has a chord line and the air foil is asymmetric about the chord line.

9. The method of claim 1 wherein the projectile has an inner flowpath that is substantially unobstructed, and the airfoil shape is symmetric about the chord line.

10. The method of claim 1 wherein the projectile is adapted and configured to be less-lethal, and the projectile has an outer diameter greater than about 35 mm and less than about 45 mm, the projectile having a blunt leading edge and a trailing edge with a distance therebetween of more than about 20 mm and less than about 35 mm;

and said propelling said projectile is with a velocity greater than about 50 m/s and less than about 150 m/s.

11. The method of claim 1 wherein the projectile is adapted and configured to be less-lethal, and the projectile has a mass of more than about 5 grams and less than about 20 grams.

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

13. The method of claim 1 wherein the projectile has an inner flowpath, a leading edge, and a trailing edge, and the inner flowpath has a minimum diameter that is located about midway between the leading edge and the trailing edge.

14. The method of claim 1 wherein the projectile has an inner flowpath, a central throat, a trailing edge, and a leading edge, and the cross sectional area of the flowpath decreases from the leading edge to the central throat, and the flow area increases from the throat toward the trailing edge.

15. The method of claim 1 wherein the projectile has a trailing edge that includes a plurality of driving features, and said spinning is by applying a torque to the driving features.

16. The method of claim 1 wherein the projectile has an outer diameter less than about 45 mm and a blunt leading edge.

17. The method of claim 1 wherein the projectile is adapted and configured to be less-lethal, and the projectile has a mass of less than about 20 grams and said propelling said projectile is with a velocity less than about 150 m/s.

18. The method of claim 1 wherein the projectile has an inner flowpath that is substantially unobstructed.