ENTANGLING PROJECTILE SYSTEM FOR THE DISABLING OF UAV'S AND OTHER TARGETS OF INTEREST

Abstract

The present invention surrounds a payload for use as a projectile for disabling and neutralizing Unmanned Aerial Vehicle (UAV) threats and the like. The payload uses a central projectile and one or more satellite projectiles tethered to central projectile. The satellite projectiles provide entangling elements. The satellite projectiles are configured to expand outward from the central projectile after firing to provide an entangling projectile system wherein any object or individual within the entangling zone of the projectile system can be ensnared and neutralized through the entangling action of the projectile system.

Claims

1. A projectile system comprising: a central projectile, and a first satellite projectile tethered to the central projectile with a first flexible line, wherein the first end of the flexible line is constrained by the central projectile, and the second end of the flexible line is interconnected to the satellite projectile; the central projectile comprises a comprises a longitudinal axis extending from a forward aspect of the central projectile toward a rearward aspect of the central projectile, wherein the longitudinal axis is parallel with an intended direction of travel of the central projectile; wherein the projectile system is configured to be fired from a barreled weapon, wherein the projectile system is configured to be in a stowed configuration prior to firing wherein the first satellite projectile is held proximal to the central projectile, and wherein the projectile system is configured to transition to a deployed configuration after firing, wherein the central projectile rotates around the longitudinal axis and centrifugal action causes the first satellite projectile to expand radially away from the central projectile.

2. The projectile system of claim 1, wherein the central projectile further comprises a first recess in an external surface of the central projectile; the first recess is configured to receive the satellite projectile therein, wherein the first satellite projectile is disposed within the first recess when in the stowed configuration, and wherein the first satellite projectile releases from the first recess in the deployed configuration.

3. The projectile system of claim 2, wherein the external surface of the central projectile comprises a circumferential surface.

4. The projectile system of claim 3, wherein the external surface of the central projectile comprises a cylindrical surface.

5. The projectile system of claim 3, further comprising a first groove extending from the first recess toward a rearward aspect of the central projectile, wherein the first groove is configured to receive the first flexible line therein.

6. The projectile system of claim 5, wherein the first groove extends toward the rearward aspect of the central projectile in a helical path.

7. The projectile system of claim 5, further comprising an annular groove in the external surface of the central projectile; the annular groove is offset toward the rearward aspect of the central projectile from the recess; and the first groove extends between the first recess and the annular groove.

8. The projectile system of claim 7, further comprising an aperture extending from the annular groove in an inner aspect of the central projectile; the aperture configured to receive the flexible line therethrough, wherein the first end of the flexible line is constrained within the inner aspect of the central projectile.

9. The projectile system of claim 8, further comprising: a plurality of satellite projectiles, each tethered to the central projectile with a flexible line; the central projectile comprising a recess for each of the plurality of satellite projectiles, wherein the recesses are angularly spaced around the central projectile; a groove extending from each of the recesses toward the rearward aspect of the central projectile, wherein each of the grooves intersects the annular groove; and a plurality of apertures through the annular groove extending inward toward the inner aspect of the central projectile, wherein each of the flexible lines is inserted therethrough and the first ends of the flexible lines are constrained within the inner aspect of the central projectile, wherein the satellite projectiles are disposed within the recess when in the stowed configuration, and wherein the satellite projectiles release from the recess in the deployed configuration.

10. The projectile system of claim 9, wherein the recesses are angularly equidistantly spaced around the external surface of the central projectile.

11. The projectile system of claim 1, comprising a plurality of satellite projectiles tethered to the central projectile, wherein each of the plurality of satellite projectiles is tethered to the central projectile with a flexible line.

12. The projectile system of claim 11, wherein the flexible lines are wrapped around the central projectile in the stowed configuration, and wherein the flexible lines unwrap due to centrifugal action in a deployed configuration.

13. The projectile system of claim 12, wherein when in a stowed configuration, the flexible lines and satellite projectiles remain within a maximum envelope of the central projectile.

14. The projectile system of claim 13, wherein the maximum envelope comprises a cylindrical form.

15. The projectile system of claim 11, further comprising a first aerodynamic feature, wherein the first aerodynamic feature is configured to induce rotation of the central projectile in a first rotational direction after firing.

16. The projectile system of claim 15, wherein the first aerodynamic feature comprises a channel.

17. The projectile system of claim 16, wherein the channel comprises a helical path around the longitudinal axis of the central projectile.

18. The projectile system of claim 17, wherein the channel extends from a medial portion offset from the longitudinal axis of the central projectile, and extends outward toward an external surface of the central projectile.

19. The projectile system of claim 18, wherein the channel extends through the external surface of the central projectile.

20. A projectile system comprising: a central projectile, and a plurality of satellite projectiles each interconnected to the central projectile with a flexible line; the flexible lines of the satellite projectiles each having a first end interconnected to the central projectile, and a second end interconnected to the satellite projectiles; the central projectile comprising a longitudinal axis extending from a forward aspect of the central projectile to a rearward aspect of the central projectile, wherein the longitudinal axis is parallel with intended direction of travel of the central projectile; a plurality of recesses in an external surface of the central projectile, wherein the recesses have the same shape as the satellite projectiles, wherein the recesses are each configured to receive one of the plurality of satellite projectiles therein; a plurality of aerodynamic channels in the central projectile extending from the forward aspect of the central projectile toward the rearward aspect of the central projectiles, wherein the plurality of aerodynamic channels have a helical path around the longitudinal axis, the aerodynamic channels are configured to induce rotation of the central projectile in a first rotational direction; a first groove in the external surface of the central projectile longitudinally offset from the recesses toward the rearward aspect; a plurality of second grooves, wherein each of the second grooves extends from one of the first groove to the plurality of recesses helically in the first rotational direction; and a plurality of apertures extending through an outer aspect of the central projectile, extending from the first groove to a cavity in an inner aspect of the central projectile, wherein the plurality of apertures are configured to permit the sliding of the flexible lines therethrough, wherein the first ends of the flexible lines are within the cavity of the central projectile, wherein the flexible lines extend from the cavity through the apertures, and wherein the flexible lines extending through the apertures are wound in the first rotational direction around the central projectile within the first groove, and the satellite projectiles are disposed within the recesses.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0028] FIG. 1— A bottom perspective view of an entangling projectile system of certain embodiments in a deployed configuration

[0029] FIG. 2A—A side view of a central projectile of certain embodiments

[0030] FIG. 2B—A top perspective view of a central projectile of certain embodiments

[0031] FIG. 2C—A bottom view of a central projectile of certain embodiments

[0032] FIG. 2D—A bottom perspective view of a central projectile of certain embodiments

[0033] FIG. 3A—A side view of a central projectile of certain embodiments

[0034] FIG. 3B—A top perspective view of a central projectile of certain embodiments

[0035] FIG. 3C—A bottom view of a central projectile of certain embodiments

[0036] FIG. 3D—A bottom perspective view of a central projectile of certain embodiments

[0037] FIG. 4—A side view of an entangling projectile system of certain embodiments in a stowed configuration

[0038] FIG. 5A—A side view of a central projectile of certain embodiments

[0039] FIG. 5B—A side section view of a central projectile of certain embodiments as shown in FIG. 4A

[0040] FIG. 6A—A side view of a central projectile of certain embodiments

[0041] FIG. 6B—A side section view of a central projectile of certain embodiments as shown in FIG. 5B

[0042] FIG. 7—A bottom view of a central projectile of certain embodiments

[0043] FIG. 8—A top perspective view of an entangling projectile system of certain embodiments in a stowed configuration

[0044] FIG. 9—A top perspective view of an entangling projectile system of certain embodiments in a deployed configuration

DETAILED DESCRIPTION OF VARIOUS EMBODIMENTS

[0045] Certain embodiments of an entangling projectile system 1000 disclosed herein, shown in FIG. 1, comprise a central projectile 1100 having a plurality of satellite projectiles 1200 each interconnected to the central projectile 1100 with a flexible line 1300. A first end 1310 of the flexible line is interconnected with the central projectile 1100, and a second end 1320 of the flexible line is interconnected with a satellite projectile 1200. Certain embodiments comprise three satellite projectiles 1200, but are not limited thereto. The satellite projectiles 1200 are configured to orbit or rotate around the central projectile 1100 at the extents of the flexible lines 1300 after leaving the barrel of a weapon from which it is fired or other means of launching.

[0046] The central projectile 1100 of certain embodiments, shown in FIG. 1-FIG. 3D comprises a longitudinal axis 1110 which extends from a forward aspect 1120 of the central projectile, to a rearward aspect 1130 of the central projectile. The central projectile 1100 of certain embodiments comprises a cylindrical shape as shown, but other shapes configured to be fired from a barreled weapon are within the spirit and scope of the present invention. The longitudinal axis 1110 is parallel with the intended direction 1140 of travel of the central projectile, and the satellite projectiles 1200 are typically configured to rotate about the longitudinal axis 1110, but are not limited thereto within the spirit and scope of the present invention.

[0047] In certain embodiments, referencing FIG. 1-FIG. 3D, the central projectile 1100 comprises a plurality of recesses 2000 in an external surface 1150 of the central projectile. The recesses 2000 are configured to have the same shape as the satellite projectiles 1200 (FIG. 1), and the recesses are configured to receive satellite projectiles 1200 therein. In certain embodiments, the recesses 2000 are configured to receive the satellite projectiles 1200 wherein the satellite projectiles 1200 do not exceed a maximum envelope 1160 of the central projectile when the satellite projectiles 1200 are held within the recesses 2000. For instance, FIG. 4 shows certain embodiments with the projectile system in a stowed configuration wherein the satellite projectiles 1200 are head within the recesses 2000. In certain embodiments, the satellite projectiles comprise a spherical or spherical dome shape wherein a spherical-dome portion of the satellite projectile is configured to have a cylindrical segment portion configured to not exceed the maximum envelope 1600 of a cylindrically shaped central projectile 1100. By matching or not exceeding the maximum envelope 1160 of the central projectile, the entangling projectile system 1000 maintains the ability to be fired from a barreled weapon.

[0048] In certain embodiments, as shown in FIG. 5A-FIG. 7, a central projectile 1100 comprises a plurality of aerodynamic channels 2100 in the central projectile wherein the aerodynamic channels 2100 are configured to induce spin to the central projectile in a first rotational direction 3000 while in flight. The aerodynamic channels 2100 of certain embodiments have a helical path around the longitudinal axis 1110. In certain embodiments as shown in FIG. 5A-FIG. 5B, the aerodynamic channels extend from a medial portion 1170 of the central projectile, offset from the longitudinal axis 1110, and extend outward toward the external surface 1150 of the central projectile, but not through the external surface 1150 of the central projectile. In alternate embodiments as shown in FIG. 6A-FIG. 6B, the aerodynamic channels 2100 extend from a medial portion 1170 of the central projectile, offset from the longitudinal axis 1110, and extend through the external surface 1150 of the central projectile. In the embodiments shown, the aerodynamic channels are configured to induce spin in a clockwise direction. However, aerodynamic channels which induce a counterclockwise spin are within the spirit and scope of the present invention. It will be appreciated by those skilled in the art that rotational directions discussed within this application are based on a view taken from a rearward aspect with the projectile system travelling away from the viewer as shown in FIG. 7.

[0049] Certain embodiments of an entangling projectile system 1000, as shown in FIG. 5A-FIG. 6B and FIG. 8, comprise a central projectile 1100 having a plurality of satellite projectiles 1200 attached thereto with flexible line 1300. The flexible line 1300 is configured to be wound around the circumference of the central projectile 1100 when in a stowed configuration 4000 (as shown in FIG. 8) prior to firing, and is configured to unwind in flight to a deployed configuration 4500 (as Shown in FIG. 1 and FIG. 9) due to a spin induced to the central projectile 1100. The central projectile 1100 of certain embodiments comprises a first groove 2200 in an external surface 1150 of the central projectile. The first groove 2200 of certain embodiments comprises an annular shape and is located proximal to the rearward aspect 1130 of the central projectile. The first groove 2200 is offset rearward from the recesses 2000 and is configured to receive the flexible line 1300 as it is wound around the central projectile 1100.

[0050] In certain embodiments, shown in FIG. 4-FIG. 8, a central projectile 1100 comprises a second groove 2300 which interconnects a recess 2000 to the first groove 2200, allowing the flexible line 1300 to be placed therein to prevent the flexible line 1300 extending between the first groove 2200 and the recess 2000 from exceeding the maximum envelope 1160 of the central projectile. In certain embodiments the second groove 2300 extends from the recess 2000 to the first groove 2200 along a helical path around the longitudinal axis 1110 in the first rotational direction 3000. In certain embodiments, each recess 2000 comprises a second groove 2300 which interconnects it to the first groove 2200 wherein the second groove 2300 extends from the first groove 2200 to the recesses 2000 in the first rotational direction 3000. It will be appreciated that although second grooves are shown having a helical path in a rotational direction consistent with the rotational spin induced by aerodynamic channels, alternate embodiments wherein the aerodynamic channels are configured to induce a spin in a first rotational direction and second grooves which extend from the first groove toward the recesses having a helical path in a second rotational direction counter to the induced spin direction, are within the spirit and scope of the present invention.

[0051] In certain embodiments, as seen in FIG. 5A-FIG. 8, a central projectile 1100 comprises a plurality of apertures 1400 which extend through an external surface 1050 of the central projectile toward an inner aspect 1500 of the central projectile. In certain embodiments, the central projectile 1100 comprises a cavity 1600 which intersects the longitudinal axis of the central projectile.

[0052] In a stowed configuration 4000, shown in FIG. 8-FIG. 9, the flexible lines of satellite projectiles are passed through the plurality of apertures 1400, and into the cavity 1600 wherein the first ends 1310 of the flexible lines terminate. The first ends 1310 of the flexible lines are constrained within the cavity 1600 with the flexible lines 1300 extending through the plurality of apertures 1400. In a stowed configuration the flexible lines 1300 are wound around the central projectile 1100 within the first groove 2200, a distal portion of the flexible lines proximate to the second end 1320 of the flexible lines are placed within the second grooves 2300, and the satellite projectiles 1200 are placed within the recesses 2000.

[0053] In certain embodiments, as shown in FIG. 9 after firing, the spin induced to the central projectile 1100 in a first rotational direction 3000, creates a centrifugal action due to inertia which results in the satellite projectiles 1200 to release from the recesses and expand outward from the central projectile 1100, thus unwinding the flexible lines 1300 from the central projectile 1100. The flexible lines 1300 unwind until the flexible lines 1300 reach their extents transforming the entangling projectile system 1000 from a stowed configuration (FIG. 8) to a deployed configuration 4500.

[0054] While various embodiments of the present invention have been described in detail, it is apparent that modifications and alterations of those embodiments will occur to those skilled in the art. However, it is to be expressly understood that such modifications and alterations are within the scope and spirit of the present invention. Further, the inventions described herein are capable of other embodiments and of being practiced or of being carried out in various ways. In addition, it is to be understood that the phraseology and terminology used herein is for the purposes of description and should not be regarded as limiting. The use of “including,” “comprising,” or “adding” and variations thereof herein are meant to encompass the items listed thereafter and equivalents thereof, as well as additional items.