Patent Publication Number: US-11047657-B2

Title: Long range large caliber frangible round for defending against UAV&#39;S

Description:
CROSS REFERENCE TO REFERENCE TO RELATED APPLICATIONS 
     This application is a continuing application of U.S. patent application Ser. No. 16/578,690 Filed on Sep. 23, 2019 which is a continuing application of U.S. patent application Ser. No. 16/367,881, filed Mar. 28, 2019 (Now U.S. Pat. No. 10,466,023), which claims the benefit of U.S. Provisional Patent Application 62/649,447 filed on Mar. 28, 2018; and U.S. Provisional Patent Application 62/716,341 filed on Aug. 8, 2018—the entire contents of which are incorporated herein by reference in its entirety for all purposes. 
    
    
     FIELD OF THE INVENTION 
     The present invention is directed to a 40 mm (1.57 in) projectile round configured to provide a large 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 present invention relates to long range shotgun shells and similar projectiles for the destruction of CLASS I and II commercial drones and other unmanned aerial vehicles. 
     BACKGROUND OF THE INVENTION 
     Unmanned Aerial Vehicles, such as CLASS I and II commercial Arial Drone Systems, herein referred to as drones, have become prevalent threats to privacy and safety in a wide variety of use cases. Until recently, the use of improvised explosive devices (IEDs) were responsible for approximately two-thirds of U.S. and Coalition casualties. Recent reports forecast that the use of weaponized drones will surpass the threat of IEDs in future conflicts. (Gouré, D. (2018, Feb. 8) [Retrieved from internet on 2018, Apr. 27] Drones will Surpass IED Threat in Future Conflicts. Retrieved from: &lt;https://www.realcleardefense.com/articles/2018/02/08/drones_to_will_surpass_ied_threat_in_f uture_conflicts_113030.html&gt;. Weaponization of drones, typically surrounds modifying a drone to allow it to carry and deliver lethal munitions. Weaponized drones have become increasingly common and pose a real and effective threat, particularly inside a range of 200 meters (656 feet) from a target. 
     Small commercial drones typically fly at altitudes below 200 meters (656 feet), and fly low and fast resulting in low exposure times. Thus, the neutralization of a drone threat is increasingly difficult as it requires detection and subsequent action. Common threat scenarios maximize the unique flight characteristics of the drones and the ability to fly low, in near proximity to the ground—whereas detection and identification of the drones is difficult. 
     Furthermore, the unauthorized use of drones has become problematic in environments such as search and rescue operations and emergency response efforts. For instance, reports of drones encroaching into airspace in the proximity of wildfires, pose a real threat to the operation of fire-fighting airplanes and helicopters. Airborne drones threaten the safety of crew aboard fire-fighting aircraft due to risk of collision, thereby grounding the fire-fighting aircraft until the drones are no longer encroaching in the airspace. 
     Due to the threat of weaponized drones, and the repeated impedance of emergency response operations there is a need for a solution for immobilizing drones with an effective range beyond the current capabilities presently available solutions. 
     SUMMARY OF THE INVENTION 
     Currently available solutions propose a variety of methods to immobilize a drone mid-flight. There is an identified need a portable solution for the immobilization of a drone which allows a user to—preferably at a range of 200 meters (656 feet) or more. 
     Many solutions have been proposed for the immobilization of a drone surrounding the use of jamming technologies, sometimes referred to as “directed energy”. Jamming technologies surround the use of electromagnetic noise at radio frequencies that drones operate and transmit video at, at a power level high enough to drown out effective communication between a drone and its pilot. A problem with such solutions surrounds the effects that jamming technologies have on surrounding infrastructure which maintains safety systems. For instance, a jammer intended to immobilize a drone can have negative effects on GPS systems as well as air traffic control. (O&#39;Donnell, Michael J. A.A.E. “To Airport Sponsor.” 26 Oct. 2016. [Retrieved from internet on 2018, May 15] Retrieved from: &lt;https://www.faa.gov/airports/airport safety/media/UAS-Counter-Measure-Testing-letter.pdf) Furthermore, such solutions may result in a drone armed with explosives continuing toward its target due to forward momentum and falling toward its intended target with an unexploded payload. Thus, the drone, even if immobilized, poses a potential threat. In some scenarios, a jammer may result in a drone initiating a “return to home” action, in which it returns toward the operator. Although in some scenarios it is advantageous to for the initiation of such an action to allow the tracking the operator of the drone, it also poses a risk. If a drone is forced to initiate a “return to home” operation, and the operator is not found, the operator may be able to reuse the drone for a subsequent action against a target. 
     The use of a jamming technology is only effective as long as the jamming technology is active and directed toward a drone which poses a threat. Because portable jammer technologies require battery power, and because they disrupt radio communications sometimes critical for safety measures, the operational lifespan of such technologies is impractical for perpetual use. Thus, a drone that poses a threat must be safely disposed of prior to ceasing jamming functions. As a result, measures must be taken to dispose of, or permanently immobilize a drone prior to ceasing jamming functions. 
     It is an aspect of certain embodiments of the present invention to mitigate unintended negative effects which solutions such as like jammers and directed energy weapons sometimes have in an urban environment. Through the use of a kinetic defeat strategy, involving the use of ballistic particles directed at a target, it will be appreciated that the nature of this invention allows it to be both as a countermeasure against mobile targets and static targets while mitigating the shortfalls associated with some directed energy solutions. 
     Solutions such as jammers require personnel to carry additional equipment. This is both costly and encumbers the personnel&#39;s mobility and ability to respond rapidly to a threat. It is an aspect of the present invention to provide effective countermeasures to immobilize and neutralize drone threats with equipment commonly carried by law enforcement and military personnel. 
     Certain solutions surround the use of a drone to counter a drone which poses a threat. Drones may be used in terror attacks in both military and civilian environments. For instance, U.S. Pat. No. 9,896,221 to Kilian (“Killian”), incorporated herein in its entirety for all purposes, is directed to a drone with a net designed to ensnare other drones. This countermeasure is both more expensive than a single anti-drone projectile of the present invention, and is limited to immobilizing a single opposing drone at a time. 
     In certain solutions, law enforcement and military personnel use traditional weapons such as a shotgun—to attempt to immobilize a drone which poses a threat. However, weapons carried by law enforcement and military personnel, such as shotguns, are decreasingly effective at immobilizing a drone beyond 40 meters (131 feet) due to range limitations. A typical characteristic of shotgun shot is an approximately 2.5 cm (1 inch) in diameter of shot pattern, per meter distance to the target. Thus, the effective impact area of shotgun shot at 40 meters (131 feet), would be expected to be 100 cm (40 in) in diameter. However, the larger the area of the effective impact area, the larger the spacing between shotgun shot. It will be appreciated that the effective impact area refers to the area encompassing the points of impact of all payload elements, such as shot pellets, against a planar object perpendicular to the trajectory of the payload. Thus, a drone beyond 40 meters may not be immobilized by on-target shotgun shot due to spacing between shot. A drone which is within 40 meters (131 feet) of a target, poses a real threat. For instance, a drone travelling at speed which is immobilized by a shotgun may still travel 40 meters (131 feet) or more before coming to rest on the ground. Thus, the use of a shotgun to eliminate a threat posed by a drone may be ineffective in preventing the drone from reaching its intended target. As a result, there is a need for a solution for immobilizing a drone with an effective impact area at a range over 40 meters (131 feet), and more preferably with at a range of 200 meters (656 feet) or more. 
     Traditional weapons which are effective at 200 meters (656 feet) or more, such as rifles, surround the use of singular projectiles that are typically less than 1.3 cm (0.5 in) in diameter. Singular projectiles are not ideal for efficient immobilization of a drone, because the effective impact area of a singular projectile is limited to the profile of the singular projectile. 
     It is an aspect of the present invention to provide a munitions round capable of having a suitable effective impact area at a range of 200 meters (656 feet). 
     Existing solutions such as those disclosed by U.S. Pat. No. 9,879,957 to Moser (“Moser”), incorporated herein in its entirety for all purposes, use simple fins and deployable wall segments to stabilize and slow portions of a round. Such solutions are insufficient, in both range and amount of shot delivered as related to immobilizing a drone. The fins and wall segments as disclosed by Moser are deployed immediately upon firing to stabilize the wad and induce drag on the wad, allowing the shot held within the wad to more effectively separate from the wad. In essence, the invention of Moser allows the adjustment of patterning as related to a 40-yard target. However, Moser does not improve the effective range of a shotgun round. 
     Technologies such as those disclosed by U.S. Pat. No. 5,936,189 to Lubbers (“Lubbers”), incorporated herein in its entirety for all purposes, discloses a general cartridge case which acts similarly to a shotgun shell which is used existing large caliber ammunition, such as the 40 mm (1.57 in) caliber utilized in this invention. The use of 40 mm (1.57 in) shotgun shells, such as the M576, is common in military and law enforcement applications. However, existing rounds are designed for defeating personnel a range of approximately 40 meters (131 feet). 
     Certain existing solutions surround the use of deployable fins for small arms to provide increased stability and accuracy for projectiles over long ranges. References such as U.S. Pat. No. 9,115,965 to Alculumbre (“Alucumbre”), incorporated herein in its entirety for all purposes, provides an example of a projectile utilizing this concept. However, Alucumbre is directed toward use with singular projectiles, such as 40 mm (1.57 in) grenades. Grenades are designed to spread fragments referred to as “flak.” While flak has a level of effectiveness in application for anti-aircraft measures, the debris pattern of flak is unpredictable and results in a significant danger when used in densely populated areas or in close proximity to unintended targets. 
     With the rising threat of terrorist attacks using drones in urban environments, there is also a rising need for counter-drone systems which can be both fully effective against drones and non-damaging to civilians and civilian property in proximity to the drone threat. Lead shot maintains kinetic energy well beyond 40 meters (131 feet) from deployment, resulting in a possibility for unintended casualties or collateral damage to unintended targets. Frangible lead-free shot, such as found in U.S. Pat. No. 9,587,918 to Burrow (“Burrow”), incorporated herein in its entirety for all purposes, can be used for the shot used in this invention. 
     Certain embodiments comprise shot using material as disclosed in U.S. Provisional Patent Application No. 62/573,632 to Folaron (“Folaron”), filed on Oct. 17, 2017, which is incorporated by reference herein in its entirety for all purposes. The frangible material of Folaron provides kinetic energy capable of destroying drones within 40 meters (131 feet) of deployment from the projectile. However, the frangible material of Folaron rapidly dissipates kinetic energy once beyond 40 meters (131 feet) from deployment such that is considered non-lethal in the event of contact with unintended targets. The material makeup of the payload of the present invention of this shot can be altered in view of Folaron, and other methods known to those skilled in the art to meet different use case requirements. 
     Certain embodiments of the present invention comprise a primer, propellant cup, fins, a mechanical timer, a segmented outer casing, and a wad loaded with frangible shot. When set to a 200-meter (656-foot) range, the round may be fired such that it travels approximately 200 meters (656 ft), prior to the shot being deployed. Upon deployment, in certain embodiments, the shot spreads in a pattern similar to that of shot deployed from a standard shotgun shell. The extended range capabilities, size of the effective impact area, combined with a larger submunition payload of this invention make it far more versatile than standard shotgun rounds, particularly in use for immobilizing drone threats. 
     Certain embodiments of the present invention utilize deployable fins to stabilize the round during flight and actuate a mechanical timer. The mechanical timer allows a user to programmably delay the deployment of the shot to result in an effective impact area similar to a standard shotgun shot at an increased range. This permits a user to tailor the effective range of the round to a particular use case. For instance, certain embodiments result in an effective impact area diameter of 100 cm (40 in) at a range of 40 meters (131 feet), when the mechanical timer is set to 0 meters (0 feet). Setting the mechanical timer of the same embodiment to 200 meters (656 feet), would result in a 100 cm (40 in) diameter effective impact area at a range of 240 meters (787 feet). 
     It is an aspect of certain embodiments to provide a delayed deployment of shot from a projectile to result in an effective impact area at an appropriate range for neutralizing a drone threat. Certain embodiments deploy the payload using a mechanical timer once the round has traveled a predetermined distance. Certain embodiments use a mechanical timer—such as disclosed by in U.S. Pat. No. 3,703,866 to Semenza (“Semenza”), incorporated herein in its entirety for all purposes—to provide the ability for a delayed deployment of shot. 
     Certain embodiments are designed to be integrated in existing defense networks against drones. Because embodiments of the present invention can be manufactured to be fired from existing weapon platforms, the present invention can be quickly and easily integrated into operational service. It is an aspect of the present invention to allow production of embodiments intended to be fired from existing weapons platforms such that security personnel are not encumbered with burdened with ancillary equipment related to drone threats. 
     Certain embodiments of the present invention are configured to be used with existing 40 mm barreled weapons and other commonly used weapons available to military and law enforcement professionals. It will be appreciated by those skilled in the art that embodiments of the present invention can be adapted to the caliber of weapons other than 40 mm weapons while in keeping with the spirit and the scope of the present invention. 
     Certain embodiments comprise an outer casing having three segments surrounding the leading portion of the projectile. The outer casing is typically composed of a polymeric compound such as polyethylene, but is not limited thereto. A propellant-cup contains a charge, comprising an appropriate amount of gunpowder or other accelerant with a primer for the initiation of the charge. The outer case keeps the round together as it is fired, prior to reaching the predetermined range and full deployment. 
     Certain embodiments comprise shot held within a shot-cup, and mechanical timer enclosed in an outer casing. External to the outer casing, a fin assembly is affixed to the trailing end of the outer casing. The fin assembly is configured to fit within the open end of a propellant cup with a wad disposed between the fin assembly and the charge. It will be appreciated by those skilled in the art that a wad surrounds a barrier which holds the powder in the bottom of the propellant and helps deploy the shot. 
     Upon firing, the fin assembly of certain embodiments radially expands and provides stabilization and axial rotation. The axial rotation also actuates the mechanical timer. The axial rotation of the fin assembly spins a threaded shaft to which the fin assembly is affixed to. The threaded shaft is engaged with an aperture of a rod-puller within the outer casing, wherein the aperture comprises female threads. The rod-puller is affixed to rods which are engaged with the segments of the outer casing. In a closed-configuration, the rods retain the segments of the outer casing in place. In an open-configuration, the rods allow the segments of the outer casing to expand radially outward and separate from the projectile. Thus, when the fin assembly rotates, the rod-puller is drawn toward the trailing end of the projectile changing the projectile from a closed-configuration to an open-configuration to deploy the payload held within the shot-cup. 
     These and other advantages will be apparent from the disclosure of the inventions contained herein. The above-described embodiments, objectives, and configurations are neither complete nor exhaustive. As will be appreciated, other embodiments of the invention are possible using, alone or in combination, one or more of the features set forth above or described in detail below. Further, this Summary is neither intended nor should it be construed as being representative of the full extent and scope of the present invention. The present invention is set forth in various levels of detail in this Summary, as well as in the attached drawings and the detailed description below, and no limitation as to the scope of the present invention is intended to either the inclusion or non-inclusion of elements, components, etc. in this Summary. Additional aspects of the present invention will become more readily apparent from the detailed description, particularly when taken together with the drawings, and the claims provided herein. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1A —a cross-sectional side view of certain embodiments 
         FIG. 1B —a perspective rear view of certain embodiments 
         FIG. 2A —a perspective rear view of certain embodiments showing undeployed fin assembly 
         FIG. 2B —a perspective rear view of certain embodiments showing deployed fin assembly 
         FIG. 3A —a perspective front view of an undeployed fin assembly of certain embodiments 
         FIG. 3B —a front view of an undeployed fin assembly of certain embodiments 
         FIG. 3C —a perspective rear view of a deployed fin assembly of certain embodiments 
         FIG. 3D —a front view of a deployed fin assembly of certain embodiments 
         FIG. 4 —a perspective view of certain embodiments having a deployed fin assembly 
         FIG. 5A —front perspective view of a deployed fin assembly of certain embodiments 
         FIG. 5B —rear perspective view of a deployed fin assembly of certain embodiments 
         FIG. 6 —exploded perspective view of certain embodiments 
         FIG. 7 —a cross-sectional side view of certain embodiments 
         FIG. 8A —perspective side view of certain embodiments showing a closed-configuration 
         FIG. 8B —perspective side view of certain embodiments showing an open-configuration 
         FIG. 9 —side view of a rod of certain embodiments 
         FIG. 10A —section view of certain embodiments 
         FIG. 10B —section view of certain embodiments 
         FIG. 11 —exploded perspective view of certain embodiments 
     
    
    
     DETAILED DESCRIPTION OF VARIOUS EMBODIMENTS 
     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&#39;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 . 
     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. 
     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 . 
     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 . 
     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. 
     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. 
     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 bearing—while 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 payloads—such as shot—contained within the outer casing  1005 , the fin assembly  1100  of certain embodiments will axially rotate faster than the outer casing  1005 . 
     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. 
     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. 
     In certain embodiments, shown in  FIG. 8A - FIG. 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. 
     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 . 
     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  1620 —having a higher inertial mass and lower aerodynamic drag than the segments  1400  and shot-cup  1600 —separates from the projectile  1000  for final deployment toward an intended target. 
     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 . 
     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. 
     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.