Abstract:
A cargo round (e.g., 155 mm high explosive projectile) is provided for dispensing submunitions. The round includes a nose tip, a casing attached thereto forming a chamber, a tail and a payload in the chamber between the tip and tail. The payload includes a plurality of axi-symmetric darts mounted on a plurality of front and rear tandem plates. Each dart has fore and aft ends along a polar axis. Each dart is shaped as a cone at its fore end and includes a cavity at its aft end. Each plate has a plurality of orifices arranged in a regular pattern. Each orifice receives a corresponding dart to protrude from both obverse and reverse sides of the plate. Each fore end of its dart in the rear plate inserts into the cavity of a counterpart dart in the front plate, and each plate shears apart on release of the payload to disperse the darts. The plates preferably have a plurality of notches arranged in rows on the reverse side, together with a lip at an outer rim and bounded recess region within the lip on the obverse side, with the orifices are disposed in the region.

Description:
STATEMENT OF GOVERNMENT INTEREST 
     The invention described was made in the performance of official duties by one or more employees of the Department of the Navy, and thus, the invention herein may be manufactured, used or licensed by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor. 
    
    
     BACKGROUND 
     The invention relates generally to submunition packaging in a cargo round. In particular, the invention provides a large plurality of flight-stabile darts for target release. 
     The 155 mm high explosive (HE) M483A1 cargo round carries a payload of dual-purpose grenades: (a) armor defeating (M42) and (b) anti-personnel (M46). Upon detonation of the primer, the flash ignites the propelling charge producing gases that eject the spin-stabilized projectile from the gun and propels the projectile to the target. The fuze, having been set to function at a pre-determined time in flight, initiates the expulsion charge ejecting the entire grenade load from the rear of the projectile. Centrifugal force from spinning disperses the grenades radially from, the projectile&#39;s line-of-flight. The M42 and M46 grenades are ground-burst submissiles that explode on impact. 
     SUMMARY 
     Conventional submunition configurations for the cargo round yield disadvantages addressed by various exemplary embodiments of the present invention. In particular, various exemplary embodiments provide a cargo round (e.g., 155 mm high explosive projectile) for dispensing submunitions. The round includes a nose tip, a casing attached thereto forming a chamber, a tail and a payload in the chamber between the tip and tail. The payload includes a plurality of axi-symmetric darts mounted on a plurality of front and rear tandem plates. 
     Each dart has fore and aft ends along a polar axis. Each dart is shaped as a cone at its fore end and includes a cavity at its aft end. Each plate has a plurality of orifices arranged in a regular pattern. Each orifice receives a corresponding dart to protrude from both obverse and reverse sides of the plate. Each fore end of its dart in the rear plate inserts into the cavity of a counterpart dart in the front plate, and each plate shears apart on release of the payload to disperse the darts. 
     In various exemplary embodiments, the plates preferably have a plurality of notches arranged in rows on the reverse side, together with a lip at an outer rim and bounded recess region within the lip on the obverse side, with the orifices are disposed in the region. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       These and various other features and aspects of various exemplary embodiments will be readily understood with reference to the following detailed description taken in conjunction with the accompanying drawings, in which like or similar numbers are used throughout, and in which: 
         FIG. 1  is an elevation view of a 155-mm cargo round; 
         FIG. 2  is an elevation view of oscillation responses; 
         FIG. 3  is a graphical view of relationship between stability factors; 
         FIG. 4  is an elevation view of a pair of stacked darts; 
         FIG. 5  is a tabular list of input parameters for dart stability; 
         FIGS. 6A-6D  are elevation views of proposed dart geometries; 
         FIG. 7  is an elevation view of a cylinder-cone dart; 
         FIG. 8  is a graphical view of cone static stability; 
         FIG. 9  is a tabular list of stability data for the cone dart; 
         FIG. 10  is a graphical view of boat-tail static stability; 
         FIG. 11  is a tabular list of stability data for the boat-tail; 
         FIG. 12  is a tabular list of stability data for witch&#39;s-hat designs; 
         FIG. 13  is a graphical view of witch&#39;s-hat static stability; 
         FIG. 14  is a graphical view of cylinder-cone static stability by material comparison; 
         FIGS. 15A-15C  are tabular lists of stability data for the cylinder-cone; 
         FIGS. 16A and 16B  are isometric views of a carrying plate; 
         FIGS. 16C through 16E  are plan and elevation views of the plate; 
         FIGS. 17A and 17B  are plan view contour plots of the plate; 
         FIG. 18  is an isometric view of an axi-symmetric wedge-model contour plot the round; and 
         FIG. 19  is a detail isometric view of the wedge-model contour plot. 
     
    
    
     DETAILED DESCRIPTION 
     In the following detailed description of exemplary embodiments of the invention, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of illustration specific exemplary embodiments in which the invention may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the invention. Other embodiments may be utilized, and logical, mechanical, and other changes may be made without departing from the spirit or scope of the present invention. The following detailed description is, therefore, not to be taken in a limiting sense, and the scope of the present invention is defined only by the appended claims. 
     Various exemplary embodiments provide an arrangement for packing and releasing a larger plurality of conical darts than available in conventional designs. The exemplary designs provide a payload of conical shaped darts that fit into the 155 mm HE projectile. The embodiments account for the stress the projectile experienced at firing-launch and in-flight. After ejecting the darts out the rear of the round, the projectile&#39;s in-flight stability is maintained to ensure maximum penetration. The embodiments thus satisfy several criteria. 
       FIG. 1  shows elevation views  100 , both upper external and lower cross-sectional, of the 155 mm HE projectile round  110 . In the A-A cross-section, the round  110  includes a truncated conical nose  120  and a shell casing  130 , which forms a cylindrical chamber. An expulsion charge  140  is disposed at the interface between the nose  120  and casing  130 . The chamber includes an empty volume  150 , a payload region  160  containing a series of cones held by plates, an empty volume  170  and a base plug  180 . 
     The darts contained within the round  110  are designed for stability upon release at a pre-determined time in flight to impact the target nose first. The material for the darts can preferably be tungsten to optimize penetration, but the reactive amalgam aluminum-teflon can also be incorporated into the design of the dart. The payload can be designed for loading a plurality of darts together. This delivery system withstands the initial forces at launch and separates upon expulsion from of the rear of the round  110 . The payload separates releasing the plates to shear apart therefore expelling the darts. The darts then strike the target set consisting of light armor vehicles, small boats, personnel, and suspected mine-fields. 
     Dart Stability: To design an effective dart, a variety of different shapes were examined between speeds of Mach 1 and Mach 2.5 to evaluate static and dynamic stability. Gyroscopic (or static) stability provides a return to the desired angle-of-attack in response to initial rotation about the yaw axis (perpendicular to the longitudinal axis). This can be quantified by the static stability condition s g &gt;1, as expressed in eqn (1) from http://www.nennstiel-ruprecht.de/bullfly/gyrocond.htm: 
                       s   g     =         (       I   x       I   y       )     ·       (       ω   ·   d       v   w       )     2     ·     (       1   ·     I   x         ρ   ·   π   ·     d   5     ·     c     M   ⁢           ⁢   α           )       &gt;   1       ,           (   1   )               
where s g  is static stability factor, I is moment of inertia for x along the polar or longitudinal axis (i.e., axial centerline) and y along the vertical transverse or equatorial axis, ω is dart angular (spin) velocity, d is dart diameter, v w  is travel velocity relative to wind, ρ is air density and c Mα  is overturning moment coefficient derivative for the azimuth angle α. In order to facilitate the dart&#39;s ability to approach the target nose first, the design may preferably avoid over-stabilization that can produce an angle-of-attack greater then 10°. The darts are assumed to be axi-symmetric.
 
     Dynamic stability represents another condition for the dart to satisfy in order to be gyroscopically stable. This can be quantified by the condition 0&lt;s d &lt;2 as expressed in eqn (2) also from http://www.nennstiel-ruprecht.de/bullfly/dynacond.htm: 
                       s   d     =     (         c     L   ⁢           ⁢   α       -         m   ·     d   2         I   x       ·     c     M     p   ⁢           ⁢   α                 c     L   ⁢           ⁢   α       -     c   D     +         m   ·     d   2         I   y       ·     (       c   mq     +     c     m   ⁢           ⁢   α         )           )       ,           (   2   )               
where s d  is dynamic stability factor, m is dart mass, c Lα  is lift coefficient, c Mpα  is magnus moment coefficient derivative, c D  is drag coefficient, c mq +c Mα  represents pitch damping moment derivative.
 
     In addition, dynamic stability requires static stability to remain below a threshold derived from dynamic stability, as expressed in eqn (3), also from the previous website: 
     
       
         
           
             
               
                 
                   
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                           s 
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                             1 
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                               s 
                               d 
                             
                           
                           ) 
                         
                       
                     
                     . 
                   
                 
               
               
                 
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     Satisfaction of a dart&#39;s dynamic stability of a dart includes dampening of oscillation about the yaw axis, with an eventual return to the initial flight-path.  FIG. 2  illustrates example elevation views  200  of an aircraft  210  having pitch oscillations, with the responses including trajectories representing positive, neutral and negative dynamic stability. For the positive stability condition  220  in which 0&lt;s d &lt;2, the flight-path  230  shows the oscillations attenuate. For the neutral stability condition  240  in which s d =2, the flight-path  250  shows the oscillations remain sinusoidal at constant amplitude. For the negative stability condition  260  in which s d &gt;2, the flight-path  270  shows the oscillation amplitude increases. 
       FIG. 3  shows a graph  300  illustrating the parametric region of dynamic stability. The abscissa  310  provides the dynamic stability parameter s d , whereas the ordinate  320  provides the static stability parameter s g . A horizontal line  330  parallel to the abscissa  310  denotes the boundary condition to satisfy static stability. A vertical line  340  together with the ordinate  320  denote the boundary conditions that asymptotically limit dynamic stability parameter s d . 
     The dynamic stability threshold boundary s g =1/s d  (2−s d ) from eqn (3) is depicted as curve  360  bounded by lines  320 ,  330  and  340 . A shaded region  370  above and inside the curve  360  identifies the region of dynamic stability, such that any point therein is stable in flight. The lower limit for static stability corresponds to s g =1 represented by a line  380 , and intersects the curve  360  at the minimum point  390 . 
     Dart Material: The reactive material aluminum-teflon may be preferred in the design of the darts, because its low density (0.2 g/cm 3 ) inert material only detonates at a high-velocity impact. Originally the material begins as powder, but forms into the desired shape under high temperature and pressure, rendering a plastic appearance and texture. Upon striking at a high velocity, the dart shears causing the aluminum and teflon to tear apart, the energy from the separation causes additional damage. One gram of this amalgam shearing at Mach 1 releases about fifteen-hundred calories of energy, equivalent to 25% of a gram of trinitrotoluene (TNT). The carbon reacts with the oxygen to release another thousand calories of energy in a sealed vessel as the penetrated target. 
     Dart Criteria: Multiple dart designs were considered, all of which required to satisfy several dimensional criteria. Dart designs for the HE round are two inches tall with a diameter of 0.34375 inch. This diameter was selected in order to fit one-hundred-fifty-one darts on a plate that can fit inside the round  110 . With this configuration there can be nineteen plates each with one-hundred-fifty-one darts, yielding a total of 2869 darts within the HE round. 
     Stacked Cones: The dart incorporates an interior conical shape. This permits 1-inch of the dart&#39;s upper portion to fit from underneath into the cavity of the dart above.  FIG. 4  shows elevation views  400  of a pair of conical darts in tandem configuration. The right side features an exterior view of a lower dart  410  inserted into the bottom cavity of an upper dart  420 . The left side illustrates a B-B cross-section with the lower dart  430  having a conical cavity  425  at the bottom, and the upper dart  440 . The nose of the lower dart  430  inserts into the corresponding cavity of the upper dart  440 . 
     The internal and external cone half-angles differ slightly from each other to prevent the nose of the lower cone  430  from jamming into the upper cone  440  above. The insertion of lower darts into upper darts reduces volume consumption as well as the dart&#39;s weight, and translates the center-of-gravity forward from a solid dart of uniform material. The preferred material is tungsten due to its greater density to enable greater penetrability. However, incorporating reactive materials into the design is also highly desirable due to enhanced effect against the target. 
     The dart is designed to satisfy static and dynamic stability between Mach 1 and Mach 2.5 flight conditions. To determine the stability characteristics of the dart, a stability and trajectory calculating program called Projectile Data Simulation (PRODAS) was employed. PRODAS is used with small projectiles, like the darts, up to the large artillery shells to calculate mass properties, aerodynamics, aero stability, trajectories, and other properties. The aero stability was the main focus for the darts, which provided the static and dynamic stability. PRODAS uses for input the geometry of the projectile followed by all the initial conditions, such as mass, density, exit muzzle velocity, initial spin rate, caliber of the gun, center of mass, and transverse and axial moments of inertia from the center of mass. 
       FIG. 5  features Table 1 to provide a list  500  of initial values as inputs into PRODAS for each test dart shape. The program then calculates the aerodynamic properties as data for display in a text document for conversion into Excel. The units are in cgs-metric to provide more precise values under the three-digit input constraint of PRODAS. The diameter, weight, axial, and trans-verse moment of inertia use the mass properties from SolidWorks. Research indicates that maximum muzzle velocity and spin rate are 792.5 m/s and 260 Hz, respectively. The rest of the conditions are provided by the program at standard temperature, pressure (STP), and density. 
     Dart Geometries: Four different axi-symmetric shapes are considered for the dart round&#39;s shape. All concepts maintained the cone shape for the fore-end, but vary at the tail end.  FIGS. 6A-6D  show elevation external views  600  of four candidate dart configurations. The original concept for the dart was an unmodified cone  610  in  FIG. 6A  with a length of 2.00 inches and a tail diameter of 0.34375 inch. The other concepts include a witch&#39;s-hat cone  620  in  FIG. 6B  with a fore-cone  622  and an aft-frustum  624 , a boat-tail  630  in  FIG. 6C  with a fore-cone  632  and a short cylindrical mid-section  634  an inverted aft-cone  636 , and a cylinder cone  640  in  FIG. 6B  with a fore-cone  642  and an aft-cylinder  644 . The fore-cones  632  and  642  of the respective boat-tail and cylinder cones  630  and  640  are both 1.8 inches in length. 
       FIG. 7  illustrates an exemplary elevation views  700  of the cylinder cone  640  in exterior and A-A cross-section. The cylinder cone dart  710  includes a tungsten nose  720  with an annular shell extending to the rear. Within the cavity formed by the shell is a reactive core plug  730 . A conical cavity  740  is disposed within the plug  730  opening rear-ward. The axes of the nose  720 , plug  730  and cavity  740  are all co-linear so that the dart  710  is axi-symmetric. Alternatively, the cylinder cone  710  can be monolithic with the same material throughout. 
     Conical Dart: A cone was selected for the original design because of its stacking ability and ease of manufacturing and mass produce-ability. An aerodynamic simulation of the cone  610  was executed in PRODAS, with the results described herein.  FIG. 8  provides a line graph  800  for static and dynamic stability of the cone dart. The abscissa  810  is Mach number and the ordinate  820  is stability factor. The legend  830  represents an upper curve  840  as static stability factor of the cone and a lower curve  850  as dynamic stability factor of the cone. An arrow  860  denotes the static threshold. 
       FIG. 9  presents Table 2 as a list  900  of parameters across the operable speed range. From Mach 1 to 2.5, the data show the conical projectile to be statically stable, with the highest stability at 3.24 (not considered overly stable). The cone&#39;s dynamic stability from Mach 1.1 through Mach 2.5 indicates a return to its original flight path in response to induced oscillation. From Mach 1 through Mach 1.05, the dart remains on its initial path unless disturbed, but without auto-correction. 
     Boat-tail Cone: The boat-tail design is commonly used in projectiles, with a cylindrical offset. An aerodynamic simulation of the boat-tail  630  was executed in PRODAS, with the results described herein.  FIG. 10  provides a static stability graph  1000  for the boat-tail. The abscissa  1010  is Mach number and the ordinate  1020  is static stability factor. Two examples of the boat-tail are compared: a first full-boat-tail version that begins the boat-tail a half of the distance from the rear of the cylinder and a second half-boat-tail version that begins the boat-tail a quarter of the distance from the rear of the cylinder. The legend  1030  represents an upper curve  1040  for the full boat-tail and a middle curve  1050  for the half-boat-tail, with the arrow  860  as static threshold. 
       FIG. 11  presents Table 3 as a pair of lists  1100  across the operable speed range: a first list  1110  of parameters for a full-boat-tail version and a second list  1120  for the half-boat-tail version. The boat-tail (in both versions) is statically stable from Mach 1 to Mach 2.5 and also dynamically stable from Mach 1 to Mach 2.5. This demonstrates that from Mach 1 to Mach 2.5 the dart remains on its flight path and maintains its desired angle-of-attack. 
     Witch&#39;s-Hat: The witch&#39;s-hat cone represents a concept intended to reduce dart mass. An aerodynamic simulation of the witch&#39;s-hat  620  was executed in PRODAS, with the results described herein.  FIG. 12  presents Table 4 as a pair of lists  1200  across the operable speed range: a first list  1210  of parameters for a small-witch&#39;s-hat version and a second list  1220  for the large-witch&#39;s-hat version. 
       FIG. 13  provides a static stability graph  1300  for the witch&#39;s-hat. The abscissa  1310  is Mach number and the ordinate  1320  is static stability factor. Two examples of the witch&#39;s-hat are compared: a first small-witch&#39;s-hat version that has a small secondary cone geometry relative to the primary cone&#39;s geometry and a second large-witch&#39;s-hat version that has a larger secondary cone geometry relative to the primary cone&#39;s geometry. The legend  1330  represents an upper curve  1340  for the full boat-tail and a middle curve  1350  for the half-boat-tail, with the arrow  860  denoting static threshold. 
     The large witch&#39;s-hat demonstrates static stable only from Mach 1.05 to Mach 1.35, but becomes unstable above this range. The small witch&#39;s-hat is statically unstable throughout the entire Mach range. This means that upon release, an induced rotation about the yaw axis does not dampen out; rather the witch&#39;s-hat dart continues to rotate, compromising likelihood of striking the target nose-first, thereby reducing accuracy and kinetic energy transfer. This instability might be due to the center-of-mass being proximate to the center-of-pressure, because without a moment to counteract the acceleration, the witch&#39;s-hat dart lacks opposing force for returning to the desired angle-of-attack, and is thus discarded for design considerations in this application. 
     Cylinder Cone: The cylinder-cone is based off a projectile shape found in some projectiles in military usage. An aerodynamic simulation of the cylinder-cone  640  was executed in PRODAS, with the results described herein.  FIG. 14  provides a graph  1400 . The abscissa  1410  is Mach number and the ordinate  1420  is static stability factor. A legend  1430  identifies lines corresponding to cylinder-cone variations. 
     Seven examples of the cylinder-cone are evaluated: a monolithic steel dart with 0.2-inch cylinder, a monolithic tungsten dart with 0.2-inch cylinder, a monolithic reactive dart with 0.2-inch cylinder, a 75%-reactive version of the cylinder, a 25%-reactive version of the cylinder, a tungsten-shell reactive plug, and a reactive cone tip. There are six variations of cylinder cone, three of which are a cylinder cone made out of steel, tungsten, or reactive material. There are also two other variations with 25% and 75% of the 0.2-inch cylinder composed of a reactive material attached to the rest of the cone. A tungsten shell wrapped around reactive material represents another variation, along with a small reactive cone placed inside the tungsten dart. 
       FIG. 14  shows the difference of static stability between steel and tungsten for the cylinder-cone dart. The abscissa  1410  is Mach number and the ordinate  1420  is static stability factor. A legend  1430  identifies lines corresponding to material variations. Three examples of the cylinder-cone designs are compared from the first, second and sixth versions, respectively: the steel version with curve  1440 , the tungsten version with curve  1450 , and a reactive version with curve  1460 , with the arrow  860  denoting static threshold. 
       FIGS. 15A through 15C  present Table 5 as a series of six lists  1500  across the operable speed range.  FIG. 15A  includes a first list  1510  of parameters for the steel version, a second list  1520  for the 0.2-inch version, and a third list  1530  for the reactive version.  FIG. 15B  includes a fourth list  1540  of parameters for the steel version, a fifth list  1550  for the 0.2-inch version, and a sixth list  1560  for the reactive version.  FIG. 15C  includes a seventh list  1570  of parameters for the steel version, a second list  1520  for the 0.2-inch version, and a third list  1530  for the reactive version. The cylinder-cone (in all versions) is statically stable from Mach 1 to Mach 2.5 and also dynamically stable from Mach 1 to Mach 2.5. This demonstrates that from Mach 1 to Mach 2.5 the cylinder-cone dart remains on its flight path and maintains the desired angle-of-attack. 
     Design Selection: Analyzing all the types of darts showed that any are a suitable for use except the witch&#39;s hat form. The original cone dart develops a large stress at a point upon launch along the bottom of the cones as stacked together. The boat-tail is both statically and dynamically stable, but may be more difficult to manufacture. Thus, the preferred choice is the cylinder-cone due to its distribution of stress along the cylinder. Moreover, the design facilitates manufacture in comparison to alternative designs. Reactive material can be disposed inside of the cylinder cone and the cylinder-cone is both statically and dynamically stable. 
     Further analysis determined that the mass of a tungsten cylinder cone exceed the carrying weight of the 155-mm cargo round. Currently the cargo round  110  is permitted to weigh only up to 104.8 pounds without fuze; to avoid damage to the gun. With almost three-thousand tungsten darts, the round would weigh up to two-hundred pounds, greatly exceeding that limit. One solution reduces the number of rows from thirteen to six, thereby reducing the carrying capacity to only 906 darts (or only ⅓ of the original) to satisfy the weight requirement. Consequently, the material of the dart was changed to alloy steel. 
     Alloy steel has about half the density of tungsten, therefore possess about half the mass for the same volume. This allows for 1963 darts out of the 2869 darts maximum to fit into the round  110  and also satisfy the weight limit. The alloy steel is not as statically stable as the tungsten dart, but both are dynamically stable from Mach 1 through Mach 2.5. The ability for the steel dart to pierce light armor and boats is expected to be less than that of tungsten, due to its lower density by comparison.  FIG. 7  shows a reactive plug inside of a tungsten shell, with a mass about the same of the steel dart, but expected to possess the penetrability of the tungsten dart. With the dart design chosen, an effective release system can be constructed. 
     Release System: The release system includes at least one plate that can hold one-hundred-fifty-one darts. These can be stacked thirteen plates high in order to stay within the weight restraint of 104.8 pounds. These holding plates not only secure the darts, but also are able to withstand the shock of launch. Upon ejection from the round  110  into the air stream, they immediately disintegrate, dispersing the darts without restraint. An expulsion cylinder holds the thirteen plates to withstand the shock of launch. The cylinder is sufficiently strong to shear the threads on the outer circumference of the cargo round base plug  180 . The threads connect the base plug  180  to the casing  130  and separate upon release into the air. 
     Design of Holding Plates:  FIGS. 16A-16E  show views of a holding plate  1600 , having a 0.2-inch thickness and composed of Aluminum Al-3003.  FIGS. 16A and 16B  show isometric views from above and below respectively,  FIG. 16C  shows a plan view from the reverse (bottom) side,  FIG. 16D  shows an elevation view showing thickness, and  FIG. 16E  shows a plan view from the obverse (top) side. Of the thickness, 0.1-inch provides a lip along the plate&#39;s top surface  1610  meant to firmly hold the top row of darts in place and the remainder 0.1-inch represents a bounded recessed region  1620  with holes  1630  to hold a lower row of darts firmly in place, of which a single example dart  710  is shown. The plate&#39;s reverse surface  1650  may include corrugation row divots or scores of 0.085-inch to facilitate fragmentation upon release from the round  110 . The cavity  740  provided at the rear of the cylindrical cone dart  710  provides a receptacle for the nose of a lower dart to be inserted. 
     The plate  1600  is designed with one-hundred-fifty-one holes  1630  in a hexagonal pattern, although other regular patterns can be contemplated. Each hole  1630  holds a corresponding dart  710  to enable the top one-inch of the dart to protrude from the top surface  1610  for insertion into the cavity  740  of the dart above on an adjacent plate  1600 . This arrangement enables adjacent tandem plates  1600  to be stacked above each other, together with their corresponding darts  710 . The top one-inch of the nose of the lower dart  410  inserts into the rear cavity  740 . Each plate  1600  can hold up to approximately three pounds of mass and withstand a centripetal force of 260 Hz and 10,000 G&#39;s of acceleration. After release from the expulsion cylinder  1830  the plates  1600  are sufficiently fragile to frangibly break apart immediately so that the darts  710  can disperse un-restrained. 
     Plate In-Flight Stress Analysis: Cosmos software is a stress analysis program in SolidWorks® used to calculate the stresses on the plate  1600 , suspended as a free-floating object with no forces applied thereto. A centripetal force of 260 Hz was then applied to simulate spinning in-flight. Lift and drag viscous forces from the air contacting the plate were not incorporated into the simulations, in order to determine whether the plate breaks merely from centripetal force as intended. 
       FIGS. 17A and 17B  present contour plots  1800 .  FIG. 17A  illustrates von Mises stresses  1710  adjacent to a stress legend  1720  (in psi). The plots  1700  indicate that the plate  1600  shears along the scores on the plate&#39;s reverse side  1650 , thereby releasing the darts  710 . The response analysis in  FIG. 17B  presents displacement responses  1730  adjacent to a strain legend  1740 . These analyses indicate that the plate tears apart, based on the relatively high displacement values solely due to centripetal force. 
     Plates Launch Stress Analysis: For the stress analysis on aluminum Al-3003 plates, Cosmos revealed that the centripetal force induced by an angular rate of 260 Hz and 10,000 G&#39;s of acceleration shears the plate  1700 .  FIG. 18  illustrates this Al-3003 result by a contour plot  1800  of an axi-symmetric wedge of the round  110  adjacent to a legend  1810 . The yield strength of aluminum Al-3003 is 6000 psi, represented by the upper value in the legend  1810 . The round  110  includes an exterior  1820  (representing the casing  130 ), a notched interior  1830 , and an aft closure  1840  (representing the tail  180 ). The interior  1830  holds an exemplary triple series of plates  1850 , one of which holds a dart  1860 . Centripetal force vectors are shown  1870  along corresponding surfaces. 
     The plates  1850  exceed 6000 psi at most their surfaces. The material of the plate was then changed to aluminum Al-2018 that has a higher yield strength of 46,000 psi. Another stress analysis executed under the same conditions.  FIG. 19  shows this Al-2018 result by a contour plot  1900  adjacent to a legend  1910 . These results showed that the plates  1950  withstand the forces  1870  of launch. The Al-2018 plate was then analyzed by itself in mid-air and the stress analysis showed that the plates  1950  do not shear with 260 Hz of centripetal force. Thus, the plate material preferably remains Aluminum Al-3003, with bands or columns can be disposed underneath the plates for additional reinforcement. Alternatively, deeper scoring on the obverse side  1650  may weaken the plate structure of Al-2018 for adequate frangibility. 
     The dart chosen, reactive plug with tungsten tip, offers the best flight stability as well as potential lethality. Upon piercing an object with the tungsten tip, the dart fractures the reactive material, thereby causing an explosion with a magnitude of 25% of a gram of TNT. With almost 2000 darts and the release system, the cargo round maintains under the maximum requirement for weight. The stress analysis shows that unreinforced plates cannot withstand the conditions at launch, but do break apart upon ejection from the round  110 . Overall, this round can be used to penetrate boats, light armor vehicles, personal and mine-fields, and to generate secondary damage from the reactive material. 
     While certain features of the embodiments of the invention have been illustrated as described herein, many modifications, substitutions, changes and equivalents will now occur to those skilled in the art. It is, therefore, to be understood that the appended claims are intended to cover all such modifications and changes as fall within the true spirit of the embodiments.