Long range large caliber frangible round for defending against UAV'S

Abstract

The present invention is directed to a projectile configured to provide a submunition payload across a wide impact pattern, similar to that of a shotgun, at a range typically beyond the capability of standard shotgun rounds. The additional range is provided in some embodiments of the invention by allowing the tailoring deployment range of the submunition payload based upon a given threat.

Claims

1. A projectile comprising: a longitudinal axis; a fin assembly at a trailing end of the projectile; the fin assembly comprising a plurality of fins, the fins distributed around a first fin mount, the fins having a connection to the first fin mount wherein the fins are radially deployable; a first end of a shaft disposed through an aperture of the first fin mount, and extending away from the fin assembly toward a leading end of the projectile; the leading end of the projectile comprising a plurality of segments forming an outer casing; and a payload comprising shot pellets constrained within the outer casing, wherein the plurality of segments are configured to separate, thereby opening the outer casing, and thereby releasing the payload from the projectile.

2. The projectile of claim 1 further comprising: a central axis; threading on the shaft; a rod-puller located between the fin assembly and the payload, the rod-puller comprising an aperture wherethrough the shaft extends through, and a plurality of rods radially offset from the aperture of the rod-puller; the aperture of the rod-puller comprising female threading configured to mate with the threading of the shaft; the rods having a first end affixed to the rod-puller, and a second end extending toward the leading end of the projectile; and each segment having a retaining feature comprising an opening configured to mate with one of the rods, wherein the projectile begins in a closed-configuration with the rods mated with the retaining features of the segments, and wherein the fins are configured to induce axial rotation to the fin assembly, thereby rotating the shaft, thereby moving the rod-puller along the central axis and disengaging the rods from the retaining features, thus changing the projectile from a closed-configuration to an open-configuration.

3. The projectile of claim 2 wherein; the rods have a diameter; the segments of the outer casing each having a retaining feature comprising an aperture with a diameter greater than the diameter of the rods; and wherein the rods are aligned with the retaining features in a closed configuration, and wherein the rods are retracted from the retaining features in an open configuration.

4. The projectile of claim 2 wherein; the rods have a first diameter and a second diameter which is less than the first diameter; the segments of the outer casing each having a first retaining feature having a groove with a diameter equal or greater than the first diameter of the rod; and the groove having a lateral opening width less than the first diameter of the rods and greater than the second diameter of the rods, wherein, for each rod, the first diameter is aligned with a corresponding one of the first retaining features in a closed configuration and the second diameter is aligned with the corresponding one of the first retaining features in an open configuration.

5. The projectile of claim 2 wherein; the rods have a first diameter at the first end of the rod, a second diameter at the second end of the rod, and a third diameter between the first diameter and the second diameter; the third diameter being smaller than the first diameter; the segments of the outer casing each having a first retaining feature having a groove with a diameter greater than the first diameter of the rods and a second retaining feature having an aperture with a diameter greater than the second diameter of the rods; the groove having a lateral opening width less than the first diameter of the rods and greater than the third diameter of the rods, wherein, for each rod, the first diameter is aligned with a corresponding one of the first retaining features and the second diameter is aligned with a corresponding one of the second retaining features in a closed configuration, and wherein, for each rod, the third diameter is aligned with the corresponding one of the first retaining features and the second diameter is retracted from the corresponding one of the second retaining features in an open configuration.

6. The projectile of claim 2, further comprising a retainer disposed between the fin assembly and the rod-puller; the retainer comprising an aperture with a bearing mounted therethrough; and the bearing having an aperture through which the shaft passes through, wherein the retainer remains rotationally static in relation to the outer casing.

7. The projectile of claim 2, further comprising a shot cup comprising a shot-cup configured to constrain the shot pellets within the outer casing prior to deployment.

8. The projectile of claim 7, wherein a closed trailing end of the shot-cup is affixed to a leading end of the shaft; and a leading end of the shot-cup comprises an open end, wherein rotation of the threaded shaft results in an outward spread of the pellets.

9. The projectile of claim 2, further comprising a propellant cup and wadding; the wadding, having a cup-shaped form surrounding the fin assembly; and the propellant cup surrounding the fin assembly and the wadding.

10. The projectile of claim 1, wherein the fins are attached to the first fin mount with a pinned connection.

11. The projectile of claim 10, further comprising a second fin mount wherein the fins are mounted between the first fin mount and the second fin mount.

12. The projectile of claim 11, further comprising torsional springs wherein a first leg of the torsional springs bears on a portion of the first fin mount, and a second leg of the torsional springs bear on the fins, wherein the torsional springs apply a force to rotate the fins radially outward from the projectile.

13. The projectile of claim 12, further comprising a bushing disposed between the first fin mount and the second fin mount; the bushing having a height configured to offset the first fin mount from the second fin mount by a distance greater than a height of the fins.

14. The projectile of claim 1, wherein the shot pellets comprise first pellets and second pellets, wherein the second pellets are larger than the first pellets.

15. The projectile of claim 14, further comprising: a second fin mount wherein the fins are mounted between the first fin mount and the second fin mount; torsional springs wherein a first leg of the torsional springs bear on a portion of the first fin mount, and a second leg of the torsional springs bear on the fins, wherein the torsional springs apply a force to rotate the fins radially outward from the projectile.

16. The projectile of claim 15, wherein the payload comprises a cylindrical form having axially located second pellets surrounded by first pellets.

17. An anti-drone projectile comprising: a fin assembly having three radially expandable fins having a pinned connection to a first fin mount and a second fin mount; the fins having a torsional spring with a first leg configured to apply force against the fins radially outward, and a second leg of the torsional spring bearing on a boss of the second fin mount; a bushing disposed between the first fin mount and the second fin mount, the bushing having a height greater than a height of the fins; a first end of a threaded shaft disposed through a central aperture of the first fin mount, through the bushing, through a central aperture of the second fin mount and extending away from the fin assembly toward a leading end of an outer casing; a retainer having a central aperture disposed around the threaded shaft proximate to a trailing end of the outer casing and a sleeve bearing disposed between the threaded shaft and the retainer; a rod-puller having a central aperture having female threads configured to mate with the threaded shaft, the central aperture of the rod-puller engaged with a portion of a leading end of the threaded shaft; a shot-cup having a payload comprising shot pellets, the shot-cup affixed to a second end of the threaded shaft; the shot pellets comprising first pellets having a first diameter, and second pellets having a second diameter, wherein the second pellets are larger than the first pellets; the rod-puller further comprising three rod-apertures radially offset equally from the central aperture at 120-degree increments; three rods each having a first end affixed to a corresponding one of the rod-apertures of the rod-puller; the rods having a first diameter consistent with a first end thereof, a second diameter consistent with a second end thereof, and a third diameter therebetween; the third diameter of the rods being less than the second diameter and the first diameter of the rods; the outer casing comprising segment each having a first retaining feature having a circular groove with a diameter greater than the first diameter of the rods, the groove having a lateral opening with a width less than the first diameter of the rods and greater than the third diameter of the rods; each segment of the outer casing having a second retaining feature having a circular aperture having a diameter greater than the second diameter of the rods; and a leading end of the segments of the outer casing configured to comprise a hemispherical form, wherein the fins are configured to induce axial rotation to the fin assembly, thereby rotating the threaded shaft, which draws the rod-puller toward the fin assembly to disengage the rods from the retaining features, thereby allowing the segments of the outer casing to expand radially outward to deploy the payload.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1Aa cross-sectional side view of certain embodiments

(2) FIG. 1Ba perspective rear view of certain embodiments

(3) FIG. 2Aa perspective rear view of certain embodiments showing undeployed fin assembly

(4) FIG. 2Ba perspective rear view of certain embodiments showing deployed fin assembly

(5) FIG. 3Aa perspective front view of an undeployed fin assembly of certain embodiments

(6) FIG. 3Ba front view of an undeployed fin assembly of certain embodiments

(7) FIG. 3Ca perspective rear view of a deployed fin assembly of certain embodiments

(8) FIG. 3Da front view of a deployed fin assembly of certain embodiments

(9) FIG. 4a perspective view of certain embodiments having a deployed fin assembly

(10) FIG. 5Afront perspective view of a deployed fin assembly of certain embodiments

(11) FIG. 5Brear perspective view of a deployed fin assembly of certain embodiments

(12) FIG. 6exploded perspective view of certain embodiments

(13) FIG. 7a cross-sectional side view of certain embodiments

(14) FIG. 8Aperspective side view of certain embodiments showing a closed-configuration

(15) FIG. 8Bperspective side view of certain embodiments showing an open-configuration

(16) FIG. 9side view of a rod of certain embodiments

(17) FIG. 10Asection view of certain embodiments

(18) FIG. 10Bsection view of certain embodiments

(19) FIG. 11exploded perspective view of certain embodiments

DETAILED DESCRIPTION OF VARIOUS EMBODIMENTS

(20) Certain embodiments comprise a projectile 1000, seen in FIG. 1A-FIG. 1B, affixed to a propellant cup 1030 with a wad 1040 therebetween. It will be appreciated by those skilled in the art that a wad, sometimes referred to as wadding, is an element used in barreled firearms to seal gas from the propellant behind a projectile, separating the charge from the projectile 1000 and transferring energy to propel the projectile 1000 and payload 1005. Wadding can be crucial to a firearm's efficiency by preventing the expanding gas from the charge from leaking past a projectile as it is being fire, ensuring that a maximum amount of energy of the charge is translated into propelling the projectile from the weapon. Wadding, as it pertains to shotgun shells, is typically a cup-shaped plastic form. It will also be appreciated by those skilled in the art that a propellant cup carries a charge of rapidly combustible material, such as gunpowder, used to propel a projectile. The propellant cup 1030 of certain embodiments further comprises a primer 1050, used to initiate a charge 1060. The initiation of the charge 1060 causes rapid combustion which results in rapid pressure increase between the wad 1040 and the propellant cup 1030, separating the projectile 1000 from the propellant cup 1030, and propelling the projectile 1000 from the weapon. Once the projectile 1000 leaves the barrel of the weapon, the wad 1040 falls away from the projectile 1000.

(21) It will be appreciated by those skilled in the art that although a projectile traditionally uses combustible material to fire a projectile from a weapon, a projectile may be alternatively fired using other means known to those skilled in the art while in keeping with the scope and spirit of the present application. Such alternatives include, but are not limited to, electromagnetic propulsion and pneumatic propulsion.

(22) In certain embodiments, shown in FIG. 2A-FIG. 2B, a projectile 1000 comprises a fin assembly 1100 comprising fins 1110 for the stabilization of the projectile 1000 while in flight. Certain embodiments comprise radially deployable fins 1110 which rotate radially outward from the projectile 1000 once the projectile leaves the barrel of the weapon from which it is fired. Certain embodiments comprise radially deployable fins 1110 which are affixed proximate to the trailing end 1020 of the projectile 1000 using a pinned connection 1130.

(23) A fin 1110, in certain embodiments (FIG. 3A-FIG. 3D), rotates radially outward about the central axis 1140 of a pinned connection 1130. In certain embodiments, a fin 1110 is fixated to the fin assembly 1100 through a pinned connection 1130 between a first fin mount 1150 and a second fin mount 1150. A fin mount of certain embodiments comprises a boss 1160, providing a mechanical stop 1165 for a spring 1180. In embodiments comprising a torsional spring 1180, a first leg 1185 of the spring 1180 bears on the fin 1110, and a second leg 1185 of the spring 1180 bears on the mechanical stop 1165, thus applying a force to rotate the fin 1110 radially outward from the projectile 1000.

(24) When the projectile 1000 (FIG. 4) leaves the barrel of a weapon, the fin 1110 is forced radially outward to a deployed position 1115 to provide stabilization. Certain embodiments of a fin 1110 are configured to induce radial rotation 1190 to the fin assembly 1100 in relation to the outer casing 1005. It will be appreciated that such radial rotation 1190 provides increased stabilization. It will be further appreciated that certain embodiments of a fin assembly 1100 may be configured to rotate clockwise or counter-clockwise rotation, while in keeping with the spirit and scope of the present invention.

(25) In certain embodiments, shown in FIG. 5A-FIG. 5B, the fin mounts 1150 are affixed to a threaded shaft 1200. In certain embodiments, the fin mounts 1150 comprise an aperture 1170. The aperture 1170 is keyed and configure to mate with the threaded shaft, to limit radial rotation of the fin assembly 1100 in relation to the threaded shaft 1200. The threaded shaft 1200 passes through apertures 1170 of the fin mounts, and a bushing 1230 disposed between a first fin mount 1150 and a second fin mount 1150. The bushing 1230 is configured to allow the retention of the fins 1110 between a first fin mount 1150 and a second fin mount 1150 without compression of the fins 1110 between the fin mounts 1150. Compression of the fins 1110 between the fin mounts 1150 would result in binding, thus restricting the fins from rotating radially outward. In certain embodiments, the distance 1240 between fin mounts 1150 is greater than the height 1120 of a fin.

(26) In certain embodiments, shown in FIG. 5A-FIG. 5B, a portion of the threaded shaft 1200 extends away from the fin assembly 1100, axially within the projectile 1000, toward the leading end 1010 of the projectile. A bearing 1310 interfaces between a portion of the threaded shaft 1200 and a retainer 1300. It will be appreciated that a bearing 1310, as used herein, surrounds a mechanical element configured to allow axial rotation with limited frictional interference. A bearing 1310 as used herein includes, but is not limited to a plain bearing, a rolling-element bearing, ball-bearing, roller-bearing, fluid bearing, jewel bearing, and a sleeve bearingwhile in keeping with the spirit and scope of the present invention. A retainer 1300 of certain embodiments is referred to as an impeller. The retainer 1300 of certain embodiments comprises a mechanical stop 1320, referencing FIG. 6-FIG. 7, configured to abut a first mechanical stop 1410 of a segment of the outer casing, extending inward from the segment 1400 of an outer casing 1005, thereby limiting the rotation of the retainer 1300 in relation to the outer casing 1005. In certain embodiments, a segment 1400 of outer casing further comprises a second mechanical stop 1410. Furthermore, rotation induced by the fin assembly 1100, rotates the fin assembly 1100 in relation to the outer casing 1005. It will be appreciated that, due to the higher mass associated with some payloadssuch as shotcontained within the outer casing 1005, the fin assembly 1100 of certain embodiments will axially rotate faster than the outer casing 1005.

(27) In certain embodiments, as seen in FIG. 8A-FIG. 8B, a leading end 1210 (FIG. 5A) of a threaded shaft is affixed to a rod-puller 1500. An aperture 1510 of the rod-puller, typically central to the rod-puller 1500, comprises female threading 1520 (not shown) configured to engage with the threaded shaft 1200, and a plurality of rods 1530 radially offset from the aperture 1510, and affixed to the rod-puller 1500. The rod-puller 1500 is engaged with a portion of the leading end 1210 of the threaded shaft. In certain embodiments, the rods 1530 are affixed to the rod-puller 1500 by way of mechanical interference fit, with rod-apertures 1540 in the rod-puller, radially offset from a centrally located aperture 1510 of the rod-puller.

(28) In certain embodiments, seen in FIG. 8A-FIG. 9, the rods 1530 further comprise a threaded end 1535 for engagement with rod-apertures 1540 in the rod-puller. In certain embodiments, the rod-puller 1500 comprises three rod-apertures 1540 which are equally offset from a centrally located aperture 1510, and radially spaced at 120-degree increments. When the fin assembly 1100 rotates in relation to the outer casing 1005, the threaded shaft 1200 is advanced further into the aperture 1510 of the rod-puller, thereby drawing the rod-puller 1500 rearward toward the fin assembly 1100. It will be appreciated that although embodiments described surround a rod-puller 1500 being drawn toward the trailing end 1020 of the projectile, a rod-puller 1500 of certain embodiments can be advanced toward the leading end 1010 of the projectile in efforts to pull or push rods 1530 to release segments 1400 of the outer casing. It will be appreciated by those skilled in the art, that the delay of deployment of payload 1610 (FIG. 6) of the present invention can be altered through the modification of one or more features. For instance, the modification of the thread pitch of the threaded shaft 1200 to comprise a coarse thread would actuate the rod-puller 1500 into an open-configuration more rapidly than a threaded shaft having a fine thread.

(29) In certain embodiments, shown in FIG. 8A-8B, the actuation of a rod-puller 1500 results in drawing the rod-puller 1500 rearward toward the trailing end 1020 of the projectile. A plurality of rods 1530 having a first end 1580 affixed to the rod-puller 1500, extend toward the leading end 1010 of the projectile from the rod-puller 1500, substantially parallel to the central axis 1090 of the projectile. When the projectile 1000 is in a closed-configuration (FIG. 8A), the rods engage with retaining features affixed to the interior surface of the segments of the outer casing. When the rod-puller 1500 is actuated, placing the projectile 1000 in an open-configuration (FIG. 8B), the rods 1530 release from retaining features 1430 on an internal aspect of the segments of the outer casing.

(30) In certain embodiments, referencing FIG. 8A-10B, a rod 1530 comprises a first diameter 1550 consistent with a first end 1580 of the rod, a second diameter 1560 consistent with a second end 1590 of the rod, and a third diameter 1570 located between the first diameter 1550 and the second diameter 1560. A first retaining feature 1430 of a segment has a groove 1440 having a substantially circular cross section configured to retain the first diameter 1550 of the rod, and the groove 1440 having a lateral opening 1450 with a width 1455 smaller than the first diameter 1550 of the rod and larger than the third diameter 1570. The second diameter 1560 of a rod engages with a second retaining feature 1430 comprising an aperture 1460 having a substantially circular cross section. Thus, when the rod-puller 1500 draws the rods 1530 rearward toward the trailing end 1020 of the projectile, the first diameter 1550 disengages from the first retaining feature 1430 and the second diameter 1560 disengages from the second retainer feature 1430. The third diameter 1570, now aligned with the first retainer feature 1430, is configured to pass through the lateral opening 1450 of the groove. Thus, the projectile transitions from a closed-configuration (FIG. 8A), to an open-configuration, and a segment 1400 of the outer casing is permitted to expand and release radially outward, separating from the projectile 1000.

(31) The projectile of certain embodiments, as seen in FIG. 11, comprises an outer casing 1005 having a plurality of segments 1400 surrounding a payload 1610. The actuation of a retaining mechanism, such as a rod-puller 1500, configures the retaining mechanism from a closed-configuration as shown in FIG. 8A, to an open-configuration as shown in FIG. 8B, releasing the segments 1400 of the outer casing. Thus, in flight, the segments 1400 of the outer casing are released, and permitted to expand radially outward from a central axis 1090 of the projectile. Upon the radial expansion of the outer casing 1005, from the central axis 1090 of the projectile, the segments 1400 create aerodynamic drag. Thus, the segments separate from the projectile, and the shot 1620having a higher inertial mass and lower aerodynamic drag than the segments 1400 and shot-cup 1600separates from the projectile 1000 for final deployment toward an intended target.

(32) The payload 1610 of certain embodiments, as seen in FIG. 11, comprises shot 1620 having a first pellet 1630 having a first diameter 1640, and a second pellet 1630 having a second diameter 1650. It will be appreciated that different size of pellets 1630 used in the same payload 1610 allows the tailoring of effective impact area of the pellets 1630. It will be appreciated by those skilled in the art that a pellet of a larger diameter will spread outward less than a pellet of smaller diameter. Thus, the smaller diameter pellets will spread outward from path of the projectile 1000 more than the pellets of larger diameter. It will be further appreciated by those skilled in the art that although the fin assembly 1100 axially rotates in relation to the outer casing 1005, the outer casing 1005 of certain embodiments also axially rotates, thus the payload 1610 also rotates axially. Due to axial rotation, the rotational inertia of the pellets 1630 of shot further induce an outward spread of pellets 1630.

(33) In certain embodiments the shot-cup 1600 is packed with shot 1620 having pellets 1630 of two different diameters: 6.35 mm (0.25 in) and 12.7 mm (0.5 in). The different diameter pellets 1630, typically in spherical form, allow for a wider dispersal and thus a larger effective impact area. It will be appreciated that embodiments can comprise pellets 1630 of different diameters than disclosed herein without departing from the spirit of scope of the present invention. Certain embodiments of the shot 1620 comprise a lead-free frangible material. The frangible and low-density nature of the shot 1620 allows it to dissipate enough kinetic energy in the event the shot 1620 does not strike an intended target. The shot-cup 1600, of certain embodiments, comprises a cylinder with an open end 1660, and a plurality of slits 1670 cut along its length. As the shot 1620 is released from the shot-cup 1600, it is deployed normally, as if fired from a standard shotgun.

(34) 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.