Patent Publication Number: US-2020300591-A1

Title: Warheads and weapons and methods including same

Description:
RELATED APPLICATION 
     The present application claims the benefit of and priority from U.S. Provisional Patent Application No. 62/821,645, filed Mar. 21, 2019, the disclosure of which is incorporated herein by reference in its entirety. 
    
    
     STATEMENT OF GOVERNMENT SUPPORT 
     This invention was made with support under Small Business Innovation Research (SBIR) Contract No. HQ0147-18-C-7426 awarded by the Missile Defense Agency (MDA). The Government has certain rights in the invention. 
    
    
     FIELD 
     The present invention relates to warheads and, more particularly, to warheads for damaging an inflight target. 
     BACKGROUND 
     Missiles and artillery launched projectiles are used to intercept and damage or destroy inflight targets such as missiles and re-entry vehicles. Known weapons for this purpose may employ a hit-to-kill vehicle or projectile, a fragmentation warhead, or a non-hit to kill, kinetic energy projectile warhead. 
     SUMMARY 
     According to some embodiments, a warhead for damaging an inflight target includes a frame system, a projectile ejection force generator, and a plurality of long rod penetrators (LRPs). The frame system has a frame lengthwise axis. The projectile ejection force generator is operative to generate an ejection force. The LRPs are mounted on the frame system. Each of the LRPs has an LRP lengthwise axis extending substantially parallel to the frame lengthwise axis. The warhead is configured such that the LRPs structurally support the frame system against axial loads on the frame system. The warhead is configured to dispense the LRPs radially outwardly using the ejection force to thereby form a matrix of the LRPs to intersect the target. 
     In some embodiments, the projectile ejection force generator is an explosive charge. 
     In some embodiments, the ratio of the total mass of the explosive charge to the total combined mass of the LRPs is less than 5 percent. 
     In some embodiments, the ratio of the total mass of the explosive charge to the total mass of the warhead is in the range of from about 0.1 percent to 5 percent. 
     In some embodiments, the frame system includes an axially extending central beam, a central cavity is defined in and extends axially through the central beam, the projectile ejection force generator is disposed in the central cavity, and the LRPs are located around the central beam. 
     In some embodiments, the frame system includes a plurality of partition walls each extending radially and axially. The partition walls are circumferentially spaced apart about the frame lengthwise axis to define a plurality of circumferentially distributed bays between the partition walls. Each of the bays contains a respective bundle of the LRPs. 
     According to some embodiments, the frame system includes a plurality of radially extending level divider walls. The level divider walls are axially spaced apart along the frame lengthwise axis to define a plurality of axially distributed levels. Each of the levels contains a respective set of the LRPs. 
     In some embodiments, each of the LRPs has opposed front and rear ends, and the front and rear ends of each LRP each engage a respective one of the level divider walls. 
     In some embodiments, the plurality of levels includes a first level containing a first set of the LRPs having a first combined mass, the plurality of levels includes a second level containing a second set of the LRPs having a second combined mass, and the second combined mass is greater than the first combined mass. 
     In some embodiments, the plurality of levels includes a first level containing a first set of the LRPs each having a first LRP length, the plurality of levels includes a second level containing a second set of the LRPs each having a second LRP length, and the second LRP length is greater than the first LRP length. 
     In some embodiments, the plurality of levels includes a first level containing a first set of the LRPs formed of a first LRP material, the plurality of levels includes a second level containing a second set of the LRPs formed of a second LRP material, and the first LRP material is different than the second LRP material. 
     According to some embodiments, the warhead includes a shell surrounding the LRPs. The LRPs are disposed radially between the frame system and the shell. The warhead further includes a plurality of rigid support inserts disposed radially between the LRPs and the shell and configured to resist buckling of the LRPs under load. 
     In some embodiments, the support inserts are formed of metal. 
     According to some embodiments, the projectile ejection force generator is an explosive charge, and the frame system includes an axially extending central beam. A central cavity is defined in and extends axially through the central beam. The explosive charge is disposed in the central cavity. The LRPs are located around the central beam. The warhead includes a shell surrounding the LRPs. The frame system includes a plurality of radially extending level divider walls. The level divider walls are axially spaced apart along the frame lengthwise axis to define a plurality of axially distributed levels. Each of the levels contains a respective set of the LRPs. The frame system includes a plurality of partition walls each extending radially and axially. The partition walls are circumferentially spaced apart about the frame lengthwise axis to define a plurality of circumferentially distributed bays between the partition walls. Each of the bays contains a respective bundle of the LRPs. 
     In some embodiments, the central beam, the level divider walls, and the partition walls form a unitary structure. 
     In some embodiments, the LRPs are disposed radially between the central beam and the shell, and the warhead further includes a plurality of rigid support inserts disposed radially between the LRPs and the shell and configured to resist buckling of the LRPs under load. 
     According to some embodiments, the frame system includes a plurality of radially extending level divider walls. The level divider walls are axially spaced apart along the frame lengthwise axis to define a plurality of axially distributed levels. Each of the levels contains a respective set of the LRPs. The frame system includes a plurality of partition walls each extending radially and axially. The partition walls are circumferentially spaced apart about the frame lengthwise axis to define a plurality of circumferentially distributed bays between the partition walls on each of the levels. Each of the bays contains a respective bundle of the LRPs. The bays defined in at least one of the levels are rotationally offset from the bays defined in another of the levels. 
     According to some embodiments, the LRPs are regular hexagonally-shaped in cross-section, and the LRPs are packed in sidewall-to-sidewall contact. 
     In some embodiments, the projectile ejection force generator includes a pressurized gas generator. In some embodiments, the projectile ejection force generator further includes an inflatable airbag configured to be inflated by pressurized gas from the pressurized gas generator. 
     In some embodiments, the projectile ejection force generator includes a spring. 
     According to some method embodiments, a method for damaging an inflight target includes providing a projectile weapon including a warhead. The warhead includes a frame system, a projectile ejection force generator, and a plurality of long rod penetrators (LRPs). The frame system has a frame lengthwise axis. The projectile ejection force generator is operative to generate an ejection force. The LRPs are mounted on the frame system. Each of the LRPs has an LRP lengthwise axis extending substantially parallel to the frame lengthwise axis. The warhead is configured such that the LRPs structurally support the frame system against axial loads on the frame system. The warhead is configured to dispense the LRPs radially outwardly using the ejection force to thereby form a matrix of the LRPs to intersect the target. The method further includes launching the weapon using artillery. 
     According to some embodiments, a warhead for damaging an inflight target includes a frame system, a projectile ejection force generator, and a plurality of long rod penetrators (LRPs). The frame system has a frame lengthwise axis. The projectile ejection force generator is operative to generate an ejection force. The LRPs are mounted on the frame system. Each of the LRPs has an LRP lengthwise axis extending substantially parallel to the frame lengthwise axis. The warhead is configured to dispense the LRPs radially outwardly using the ejection force to thereby form a matrix of the LRPs to intersect the target. The frame system includes a plurality of partition walls each extending radially and axially. The partition walls are circumferentially spaced apart about the frame lengthwise axis to define a plurality of circumferentially distributed bays between the partition walls. Each of the bays contains a respective bundle of the LRPs. 
     In some embodiments, the projectile ejection force generator is an explosive charge. The frame system includes an axially extending central beam. A central cavity is defined in and extends axially through the central beam. The explosive charge is disposed in the central cavity. The LRPs are located around the central beam. The warhead includes a shell surrounding the LRPs. The frame system includes a plurality of radially extending level divider walls. The level divider walls are axially spaced apart along the frame lengthwise axis to define a plurality of axially distributed levels. Each of the levels contains a respective set of the LRPs. 
     In some embodiments, the central beam, the level divider walls, and the partition walls form a unitary structure. 
     In some embodiments, the LRPs are disposed radially between the central beam and the shell. The warhead further includes a plurality of rigid support inserts disposed radially between the LRPs and the shell and configured to resist buckling of the LRPs under load. 
     According to some embodiments, a warhead for damaging an inflight target includes a frame system, a projectile ejection force generator, and a plurality of long rod penetrators (LRPs). The frame system has a frame lengthwise axis. The projectile ejection force generator is operative to generate an ejection force. The LRPs are mounted on the frame system. Each of the LRPs has an LRP lengthwise axis extending substantially parallel to the frame lengthwise axis. The warhead is configured to dispense the LRPs radially outwardly using the ejection force to thereby form a matrix of the LRPs to intersect the target. The warhead includes a shell surrounding the LRPs. The LRPs are disposed radially between the frame system and the shell. The warhead further includes a plurality of rigid support inserts disposed radially between the LRPs and the shell and configured to resist buckling of the LRPs under load. 
     According to some embodiments, a warhead for damaging an inflight target includes a frame system, a projectile ejection force generator, and a plurality of long rod penetrators (LRPs). The frame system has a frame lengthwise axis. The projectile ejection force generator is operative to generate an ejection force. The LRPs are mounted on the frame system. Each of the LRPs has an LRP lengthwise axis extending substantially parallel to the frame lengthwise axis. The warhead is configured to dispense the LRPs radially outwardly using the ejection force to thereby form a matrix of the LRPs to intersect the target. The LRPs are regular hexagonally-shaped in cross-section. The LRPs are packed in sidewall to sidewall contact. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The accompanying figures are included to provide a further understanding of the present invention, and are incorporated in and constitute a part of this specification. The drawings illustrate some embodiments of the present invention and, together with the description, serve to explain principles of the present invention. 
         FIG. 1  is a schematic view of a weapon system including a projectile weapon according to embodiments of the invention, wherein the projectile weapon has been exploded to damage an inflight target. 
         FIG. 2A  is a schematic, side view of the exploded projectile weapon of  FIG. 1 . 
         FIG. 2B  is a schematic, end view of the exploded projectile weapon of  FIG. 1 . 
         FIG. 3  is a front perspective view of the weapon of  FIG. 1 . 
         FIG. 4  is a cross-sectional view of the projectile weapon of  FIG. 1  taken along the line  4 - 4  of  FIG. 3 . 
         FIG. 5A  is a cross-sectional view of the projectile weapon of  FIG. 1  taken along the line A-A of  FIG. 4 . 
         FIG. 5B  is a cross-sectional view of the projectile weapon of  FIG. 1  taken along the line B-B of  FIG. 4 . 
         FIG. 5C  is a cross-sectional view of the projectile weapon of  FIG. 1  taken along the line C-C of  FIG. 4 . 
         FIG. 5D  is a cross-sectional view of the projectile weapon of  FIG. 1  taken along the line D-D of  FIG. 4 . 
         FIG. 5E  is a cross-sectional view of the projectile weapon of  FIG. 1  taken along the line E-E of  FIG. 4 . 
         FIG. 6  is a fragmentary, front perspective view of a warhead forming a part of the projectile weapon of  FIG. 1 . 
         FIG. 7  is an exploded, front perspective view of the warhead of  FIG. 6 . 
         FIG. 8  is a front perspective view of a long rod projectile forming a part of the warhead of  FIG. 6 . 
         FIG. 9  is an end view of the long rod projectile of  FIG. 8 . 
         FIG. 10  is an end view of a support insert forming a part of the warhead of  FIG. 6 . 
         FIG. 11  is a perspective view of the support insert of  FIG. 10 . 
         FIG. 12  is a fragmentary, front perspective view of a warhead according to further embodiments. 
         FIG. 13  is a front perspective view of a frame system forming a part of the warhead of  FIG. 12 . 
     
    
    
     DESCRIPTION 
     The present invention now will be described more fully hereinafter with reference to the accompanying drawings, in which illustrative embodiments of the invention are shown. In the drawings, the relative sizes of regions or features may be exaggerated for clarity. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. 
     It will be understood that when an element is referred to as being “coupled” or “connected” to another element, it can be directly coupled or connected to the other element or intervening elements may also be present. In contrast, when an element is referred to as being “directly coupled” or “directly connected” to another element, there are no intervening elements present. Like numbers refer to like elements throughout. 
     In addition, spatially relative terms, such as “under”, “below”, “lower”, “over”, “upper” and the like, may be used herein for ease of description to describe one element or feature&#39;s relationship to another element(s) or feature(s) as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as “under” or “beneath” other elements or features would then be oriented “over” the other elements or features. Thus, the exemplary term “under” can encompass both an orientation of over and under. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly. 
     Well-known functions or constructions may not be described in detail for brevity and/or clarity. 
     As used herein the expression “and/or” includes any and all combinations of one or more of the associated listed items. 
     The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. 
     Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein. 
     As used herein, “monolithic” means an object that is a single, unitary piece formed or composed of a material without joints or seams. 
     The term “automatically” means that the operation is substantially, and may be entirely, carried out without human or manual input, and can be programmatically directed or carried out. 
     The term “programmatically” refers to operations directed and/or primarily carried out electronically by computer program modules, code and/or instructions. 
     The term “electronically” includes both wireless and wired connections between components. 
     Some embodiments of the invention are directed to anti-missile weapons. In particular, weapons as disclosed herein may be used in accordance with methods of the invention to defend against, damage and destroy ballistic missiles, cruise missiles, and re-entry vehicles such as ballistic missile re-entry vehicles (BMRV). Weapons as disclosed herein may be used in accordance with methods of the invention to defend against, damage and destroy drones and other aircraft. 
     Weapons and warheads according to some embodiments are adapted for and used as artillery launched projectiles. In some embodiments, the artillery launched projectile is a hypervelocity projectile (HVP). 
     In other embodiments, the warhead is mounted on an airborne vehicle. In some embodiments, the warhead is mounted on a navigable vehicle. In some embodiments, the warhead is mounted on a missile or rocket. 
     Warheads according to some embodiments, and projectiles including said warheads, are particularly contemplated for use as non-hit to kill warheads that attack an inflight target (e.g., missile) using a standoff engagement between the warhead and the target. In some embodiments, the warhead is not a blast fragmentation or hit to kill warhead. In other embodiments, the warhead or weapon may also incorporate a blast fragmentation or hit to kill component or system, in which case the mechanisms disclosed herein are in addition to or supplemental to the blast fragmentation or hit to kill component. 
     In general, a warhead according to embodiments of the invention is a kinetic energy projectile warhead that uses kinetic energy projectiles (in some embodiments, long rod penetrators (LRPs)) to inflict damage on a high velocity target in flight. When the warhead is proximate to the predicted path of the target, the warhead detonates an explosive of the warhead. The detonation of the explosive forcibly disperses the projectiles into a collection, set, distribution, “wall” or matrix of the projectiles in space. The matrix may have a generally prescribed pattern. The target then flies through the projectile matrix so that the target strikes at least one of the projectiles. The kinetic energy of the high velocity target causes high energy impacts between the target and the projectiles of the matrix, thereby damaging the target. In some cases, these high energy impacts will cause the projectiles to penetrate the target. 
     In some embodiments, a relatively small amount of explosive is employed in the warhead so that the projectiles are essentially pushed out from stored or ready positions in the warhead into the matrix. In this case, the warhead does not rely predominantly on the kinetic energy of the dispersed projectiles to damage the target (e.g., as in the case of a blast fragmentation warhead). Rather, the warhead predominantly uses the kinetic energy of the target to damage the target. 
     In some embodiments, the warhead as described uses a non-hit to kill, standoff engagement with the target. In this case, the trajectory or path of the undetonated warhead does not or may not intersect the trajectory or path of the target. Instead, the explosive dispensation and dispersal of the projectiles spreads the projectiles into the path of the target. 
     Warheads according embodiments of the invention can provide a number of advantages. By presenting a spatially wide field of projectiles, the warhead increases the likelihood that it will intercept and disable the target. The warhead requires less explosive in the warhead, which provides improved safety, weight savings, and compactness of the warhead. In particular, the reduced explosive can provide a lower mass of explosive to overall mass of warhead ratio. 
     With reference to  FIGS. 1-11 , a weapon system  10  ( FIG. 1 ) according to some embodiments is shown therein. The weapon system  10  includes an artillery  20  and a projectile weapon  50 . The weapon  50  includes a warhead  100  according to embodiments of the invention. 
     The weapon system  10 , the weapon  50 , and the warhead  100  may be used as follows in accordance with some embodiments. The artillery  20  is used to launch the weapon  50  such that the weapon  50  flies along a weapon path FW in a forward flight direction F and comes into close proximity to an in-flight target M progressing along a target path FT. As discussed herein, the warhead  100  explodes and thereby disperses a wall or matrix W of projectiles  150  prior to encountering the target M. According to some embodiments and as illustrated in the figures, the projectiles are long rod projectiles (LRPs)  150 . As the target M passes the exploded warhead  100 , the target M flies through the matrix W and collides with one or more of the dispersed LRPs  150 . The kinetic energy of the target M is applied to the intercepting LRPs  150  so that the LRPs  150  inflict damage on the target M. The target M may be a missile, a re-entry vehicle (e.g., ballistic missile re-entry vehicle), or other inflight vehicle, for example. The vehicle may be a manned aircraft or an unmanned aircraft (drone or aerial unmanned autonomous vehicle (UAV)). 
     The artillery  20  may be any suitable apparatus for launching the weapon  50  as described herein. As used herein, “artillery” means a projectile firing weapon including a propulsion mechanism and configured to shoot a projectile along an unpowered trajectory using a propulsion force generated by the propulsion mechanism of the artillery. In some embodiments, the artillery  20  is a tube-launched projectile firing weapon. In some embodiments, the artillery  20  is a cannon. In some embodiments, the artillery  20  is a large gun or cannon that propels the weapon  50  by exploding a propellant charge in the artillery  20 . In some embodiments, the artillery  20  is a railgun that uses electromagnetic force in the artillery  20  to propel and launch the weapon  50  (e.g., by accelerating an armature forming a part of the weapon or a separate armature configured to displace the weapon  50 ). 
     The artillery  20  may be mounted in any suitable manner for fixed operation or mobile operation. The artillery  20  may be configured for and used on land, on water (e.g., at sea), or in air. In some embodiments, the artillery  20  is mounted on or conveyed by a land-based vehicle. In some embodiments, the land-based vehicle is a tank. In some embodiments, the artillery  20  is mounted on a watercraft (e.g., a warship). 
     The exemplary artillery  20  shown in  FIG. 1  includes a cannon including a barrel  22  and a propulsion mechanism  24 . The barrel  22  has a terminal opening  22 A through which the weapon  50  is ejected. The propulsion mechanism  24  may include, for example, artillery propellant. 
     The weapon  50  includes a front end  52 A and an opposing rear end  52 B and defines a lengthwise axis J-J. The weapon  50  has a tail section  54  on the rear end  52 B, and a nose  56  on the front end  52 A. The warhead  100  is mounted between the tail section  54  and the nose  56 . The weapon  50  may also include an onboard control system  60 . The control system  60  may be operative to selectively control the detonation of the warhead  100  as described herein. In some embodiments, the on-board system  60  is operative to automatically, programmatically and electronically detonate the warhead  100 . The control system  60  may also be operative to communicate with a remote terminal or controller and or to control guidance of the weapon  50 . 
     The warhead  100  defines a lengthwise war head central axis A-A. The warhead  100  has a front end  102 A and an opposing rear end  102 B. The warhead  100  includes a support system  110 , a plurality of LRPs (referred to herein collectively as the LRPs  150 ), and a projectile ejection force generator in the form of an expelling charge and, more particularly, in the form of an explosive charge  140 . 
     The support system  110  includes a tubular shell  112  defining an internal chamber  112 A. The support system  110  further includes a frame system or truss  120  and a plurality of support members or inserts  114 . 
     The frame system  120  has a lengthwise axis E-E. The frame system  120  includes a central beam  122  extending from a front end  122 A to a rear end  122 B. The frame system  120  further includes a front wall  128 , a rear wall  129 , multiple level divider walls  130 , and multiple circumferential partition walls  132 . 
     The central beam  122  extends continuously from the rear wall  129  to the front end  120 A. The central beam  122  is tubular and defines a central cavity  124  extending the length of the central beam  122 . In some embodiments and as shown, the central cavity  124  is cylindrical. In some embodiments and as shown, the outer surface of the central beam  122  is faceted and has substantially planar outer surfaces  125 . 
     The rear wall  129  and the level divider walls  130  are substantially planar. The rear wall  129  and the level divider walls  130  each extend substantially orthogonal to the axis E-E and project radially outwardly from the central beam  122 . 
     The partition walls  132  are substantially planar. The partition walls  132  each extend axially substantially parallel to the axis E-E and project radially outwardly from the central beam  122 . The partition walls  132  collectively form three beams (extending axially, and circumferentially spaced apart about the frame axis E-E) of the triple beam or tribeam axial load support structure  120 . 
     In some embodiments, each wall  128 ,  129 ,  130  extends fully from the central beam  122  to the shell  112 . In some embodiments, each partition wall  132  extends fully from the central beam  122  to the shell  112 , and also extends fully from the adjacent rearward divider wall  129  or  130  to the adjacent forward divider wall  128  or  130 . 
     The rear wall  129  and the level divider walls  130  each define a respective tier or level T 1 -T 5  between the wall  129  or level divider wall  130  and the next wall  128  or level divider wall  130 . Each level T 1 -T 5  includes three partition walls  132  that divide the level T 1 -T 5  into three circumferentially distributed bays B. Thus, the tiers T 1 -T 5  are serially axially distributed along the frame axis E-E, and the bays B are serially circumferentially distributed about the frame axis E-E. As shown and discussed below, each bay B contains a plurality of the LRPs  150  and one or more of the support inserts  114 . 
     The shell  112  surrounds the bays B so that the shell  112  and the frame system  120  together form five canisters C 1 -C 5 . Each canister C 1 -C 5  includes a respective one of the levels T 1 -T 5  and the LRPs  150  and support inserts  114  contained therein. 
     Additionally, each canister C 1 -C 5  is subdivided into three bay subcanisters, housings or enclosures DC ( FIG. 5E ) by the three partition walls  132  in the respective canister C 1 -C 5 . Each of these bay enclosures DC surrounds and defines a respective one of the bays B and is defined by a section of the shell  112 , opposed end or divider walls  128 ,  130 ,  129 , and opposed partition walls  132 . As discussed below, each bay enclosure DC contains a bundle of the LRPs  150 , and a support insert  114 . 
     Each support insert  114  includes opposed end faces  115 , an axially and circumferentially extending outer surface  116 , and an axially and circumferentially extending inner surface  118 . The outer surface  116  is contoured to substantially conform to the shape of the inner surface of the shell  112 . The outer surface  116  may be directly attached to the shell  112 . The inner surface  118  is contoured to substantially conform to the shapes of the LRPs  150  immediately adjacent the inner surface  118 . 
     The support inserts  114  may be formed of any suitable rigid material. In some embodiments, each support insert  114  is formed of metal. In some embodiments, the support inserts  114  are formed of titanium. In some embodiments, the support inserts  114  are 3D printed. 
     The shell  112  may be formed of any suitable rigid material. In some embodiments, the shell  112  is formed of a metal. In some embodiments, the shell  112  is formed of titanium. 
     The frame system  120  may be formed of any suitable rigid material. In some embodiments, the frame system  120  is formed of a metal. In some embodiments, the frame system  120  is formed of titanium. 
     In some embodiments, the central beam  122 , the front wall  128 , the rear wall  129 , the level divider walls  130 , and the circumferential partition walls  132  are constructed as a rigid, unitary member. In some embodiments, the central beam  122 , the front wall  128 , the rear wall  129 , the level divider walls  130 , and the partition walls  132  are a monolithic component. 
     In other embodiments, one or more of the components  122 ,  130 ,  132  may be movably mounted on the others. For example, in some alternative embodiments, the circumferential partition walls  132  may be mounted such that they can float relative to the beam  122 . In some alternative embodiments, one or more of the level divider walls  130  may be mounted such that they can float relative to the beam  122 . 
     In some embodiments, the thickness N 1  ( FIG. 4 ) of the shell  112  is in the range of from about 0.15 cm to 0.5 cm. 
     In some embodiments, the thickness N 2  ( FIG. 4 ) of the sidewall of the central beam  122  is in the range of from about 0.1 cm to 0.5 cm. 
     In some embodiments, the inner diameter D 2  ( FIG. 7 ) of the central cavity  124  is in the range of from about 0.5 cm to 2.5 cm. 
     In some embodiments, the thickness N 3  ( FIG. 4 ) of the each level divider wall  130  is in the range of from about 0.1 cm to 0.5 cm. 
     In some embodiments, the thickness N 4  ( FIG. 5D ) of the each partition wall  132  is in the range of from about 0.1 cm to 0.5 cm. 
     In some embodiments, each level T 1 -T 5  has a height  116  ( FIG. 4 ; i.e., the axial distance between the inner surfaces of the walls  128 ,  129 ,  130  defining the respective level T 1 -T 5 ) in the range of from about 4.5 cm to 9 cm. The heights  116  of the levels T 1 -T 5  may be different from one another. 
     The LRPs  150  include a first set of LRPs  151  contained in the bays B of the first level T 1 , a second set of LRPs  152  contained in the bays B of the second level T 2 , a third set of LRPs  153  contained in the bays B of the third level T 3 , a fourth set of LRPs  154  contained in the bays B of the fourth level T 4 , and a fifth set of LRPs  155  contained in the bays B of the fifth level T 5 . 
     The LRPs  151 - 155  are assembled as subsets or bundles G of LRPs  150  in each bay B. 
     More particularly, each set of LRPs  151 - 155  is subdivided into three circumferentially distributed subsets or bundles G of LRPs  150 , and each of these bundles G is contained in a respective one of the bays B. For example, as shown in  FIG. 5E , the level T 5  includes three circumferentially distributed bundles GA, GB, GC of the LRPs  155 , and each of these bundles GA, GB, GC is disposed in a respective one of the bay enclosures DC. 
     According to some embodiments and as shown, the LRPs  150  are each individually preformed. One of the LRPs  155  will be described in more detail hereinbelow. It will be appreciated that this description likewise applies to the other LRPs  151 - 155 . However, it will also be appreciated that the LRPs  151 - 155  of each level T 1 -T 5  may differ from the LRPs  151 - 155  of another level T 1 -T 5  in one or more respects. For example, LRPs in each level T 1 -T 5  may differ from one another in shape, length, weight, and/or material. 
     The LRP  155  is a long rod penetrator (LRP) and has a lengthwise axis I-I and extends axially from a front end  160 A to a rear end  160 B. The LRP  155  has side faces  164  distributed circumferentially about the axis I-I, and end faces  166  on either end  160 A,  160 B. 
     In some embodiments, the side faces  164  are substantially planar. In some embodiments and as shown, the LRP  155  has a regular hexagonal cross-sectional shape. In some embodiments, each of the end faces  166  is substantially planar. In some embodiments, the side face of the LRP  155  is cylindrical. 
     In some embodiments, each LRP  150  has a length L 1  ( FIG. 8 ) in the range of from about 1.5 cm to 6 cm. 
     In some embodiments, each LRP  150  has a diameter D 1  ( FIG. 9 ) in the range of from about 0.25 cm to 1.5 cm. 
     In some embodiments, the ratio of the length L 1  ( FIG. 8 ) of each LRP  150  to its diameter D 1  ( FIG. 9 ) is at least 3:1 and, in some embodiments, is in the range of from about 3:1 to 24:1. 
     In some embodiments, each LRP  150  has a weight of at least 1 gram and, in some embodiments, in the range of from about 15 grams to 165 grams. 
     The LRPs  150  may be formed of any suitable rigid material. In some embodiments, each LRP  150  is formed from a material having a high sectional density to increase penetration performance. In some embodiments, some or all of the LRPs  150  are formed of metal. In some embodiments, some or all of the LRPs  150  are formed of tungsten. 
     The LRPs  151 - 155  may have different dimensions (length and diameter), shapes, and materials from one another. 
     As illustrated in  FIGS. 4-6 , the LRPs  151 - 155  are packed in each bay B about the central beam  122 . The LRPs  151 - 155  are oriented such that their lengthwise axes I-I are parallel with the warhead lengthwise axis A-A and the frame system lengthwise axis E-E. The support inserts  114  are in turn packed around the LRPs  151 - 155 . The shell  112  is in turn installed about the inserts  114 . The inner surfaces  118  of the support inserts  114  are shaped to conform to the irregular shape of the LRP bundle G in each bay B.  FIGS. 5A-5E  are cross-sectional views of the warhead  100  taken along the lines  5 A- 5 A,  5 B- 5 B,  5 C- 5 C,  5 D- 5 D and  5 E- 5 E, respectively. 
     One or more of the bays B may contain LRPs that are axially stacked (end  166  to end  166 ) on one another in the bay. Such an arrangement is shown for the LRPs  151  in the bays B of the first level T 1 . Each of the stacks includes three LRPs  151 . 
     In some embodiments, in the foregoing manner, substantially all of the free space in each canister C 1 -C 5  or bay enclosure DC is occupied by rigid components (i.e., the LRPs  151 - 155  and the support inserts  114 ). The LRPs  151 - 155  are firmly secured in face  164  to face  164  contact with one another and with the partition walls  132  and the central beam outer faces  125 . 
     In some embodiments, each support insert  114  is firmly secured with its outer surface  116  in contact with the shell  112 , its inner surface  118  in contact with the LRPs  150 , and its end faces  115  in contact with the adjacent walls  128 ,  129 ,  130 . 
     In some embodiments, the fit between the ends  166  of the LRPs  150  and the level divider walls  130  is snug or tight with well controlled tolerance across all of the LRPs  150  to avoid creating uneven stress distributions. In some embodiments, the height  116  of each level T 2 -T 5  is no more than (i.e., the permitted tolerance) 2 mm greater than the length L 1  of the LRPs  152 - 155  disposed in that level T 2 -T 5 . In the case of the level T 1 , the height  116  of the level T 1  is no more than 2 mm greater than the total length L 8  ( FIG. 7 ) of each axial stack of the LRPs  151  (i.e., the axial, end-to-end stack of three LRPs  151 ). In some embodiments, both end faces  166  of each LRP  152 - 155  are held in firm or mating contact with the adjacent walls  129 ,  130  defining the level containing the LRP. Similarly, in some embodiments, the endmost faces  166  of the LRPs  151  in an LRP stack are held in firm or mating contact with the adjacent walls  128 ,  130  defining the level T 1 . 
     The explosive charge  140  is disposed in and fills the length of the central beam cavity  124  from a front end  140 A to a rear end  140 B. In some embodiments and as shown, the explosive charge  140  extends from the rear wall  129  to a front-end wall  127 . In some embodiments and as shown, the explosive charge  140  extends only through part of the height of the first level T 1  so that a portion  124 A of the cavity  124  does not contain explosive. In some embodiments, the explosive charge  140  has a substantially uniform cross-sectional area from end  140 A to end  140 B. 
     Any suitable explosive may be used for the explosive charge  140 . In some embodiments, the explosive charge  140  is a high energy (HE) explosive. Suitable explosives may include plastic bonded military grade types, including, PBXN-109, PBXN-110, CL-20, AFX-757, Composition B, or C4. 
     In some embodiments, the explosive charge  140  is a low explosive (LE) charge. A low explosive is a chemical mixture that deflagrates. That is, the low explosive material explodes in the form of subsonic combustion propagating through heat transfer, with hot burning low explosive material heating the next layer of the cold low explosive material and igniting it. The exploding low explosive changes into gas by rapidly burning or combusting without generating a high pressure wave as generated by detonation of a high explosive. The rate of combustion of a low explosive is less than 632 meters/second. 
     As discussed above, in use in accordance with some embodiments, the weapon  50  is launched from the artillery  20  such that the weapon  50  flies into proximity with the target M. The propulsion mechanism  24  of the artillery  20  applies a large launch force to the weapon  50  that forces the weapon  50  through the barrel  22  and the terminal opening  22 A in the forward direction F. The weapon  50  is thereby propelled by the artillery  20  to travel the weapon flight path FW. In some embodiments, the weapon  50  travels the flight path without the aid of onboard propulsion. Prior to coming into close proximity to the target M, the control system  60  detonates the explosive charge  140 . For example, the control system  60  may detonate the explosive charge  140  a prescribed period of time prior to the closest proximity between the flight paths FW and FT. In some embodiments, the detonation of the explosive charge  140  is initiated at the rear end  140 B and propagates progressively from the rear end  140 B the front end  140 A. 
     Upon detonation, the HE explosive charge  140  generates gas pressure and shock waves that eject, drive or project the LRPs  151 - 155  radially outward in radial directions R (i.e., circumferentially distributed azimuthal directions relative to the axis A-A). The LRPs  151 ,  152 ,  153 ,  154  and  155  of each canister C 1 -C 5  or level T 1 -T 5  are projected in radial projection patterns P 1 , P 2 , P 3 , P 4  and P 5 , respectively ( FIG. 2A ) circumferentially about axis A-A. The combination of the radial projection patterns P 1 -P 5  forms a combined projection pattern PC ( FIGS. 2 and 3 ) (extending 360 degrees circumferentially about the axis A-A). The shell  112  may be blown off or disintegrated, but typically will not significantly affect the paths or energies of the LRPs  151 - 155 . 
       FIG. 2A  is a side view of the exploded weapon  50  at a first time after the detonation of the explosive charge  140 , and  FIG. 2B  is a front-end view of the weapon  50  at this first time. 
     The dispensed LRPs  151 - 155  will thus form a wall or matrix W of the LRPs  151 - 155  that extends circumferentially outwardly from the axis A-A. The detonation of the explosive charge  140  is timed such that the target M will fly through this matrix W. It will be appreciated that the matrix W will spatially expand as a function of time, and the detonation of the explosive charge  140  may be timed to achieve a prescribed or preferred pattern PC at the time of intersection between the target M and the matrix W. 
     The warhead  100  is configured such that the long rod penetrators  151 - 155  continue to be oriented with their lengthwise axes I-I substantially or generally parallel to the axis A-A. In some embodiments, the axis A-A is substantially parallel with the direction of travel of the weapon  50  at the time of detonation of the explosive charge  140 . In this way, the LRPs  151 - 155  will tend to initially impact the target M with their front ends  160 A and end faces  166 . This may help to more efficiently inflict damage on the target M, including by penetrating the target M. 
     In some embodiments, the dispensed the LRPs  150  are ejected from the bays B at a velocity of less than 1000 m/s and, in some embodiments, at a velocity in the range of from about 100 m/s to 1000 m/s. 
     Various aspects of the warhead  100  may be selected to determine the shapes of the patterns P 1 -P 5 , PC. 
     The weapon  50  and the warhead  100  may be particularly well-suited for launching using artillery (e.g., cannon) or a gun. 
     Because the warhead  100  is used as a non-hit to kill warhead, it can be constructed using a relatively small amount of explosive. In some embodiments, the explosive charge  140  is an HE explosive and the ratio the mass of the explosive charge  140  to the combined masses of the LRPs  151 - 155  is less than 5%. In some embodiments, the explosive charge  140  is an HE explosive and the ratio the mass of the warhead  100  as a whole (including all of the LRPs  150 , the support system  110  and the support inserts  114 ) to the mass of the explosive charge  140  is in the range of from about 0.1% to 5%. 
     The warhead  100  must survive the high acceleration of launching from an artillery cannon. Because the weapon  50  must be rapidly accelerated in order to complete the flight path FW, the weapon  50  (including the frame system  120 ) is subjected to large launch loading along the weapon lengthwise axis J-J, the warhead central axis A-A, and the frame lengthwise axis E-E. The launch loading requirement on the warhead  100  when launching the weapon  50  from artillery is drastically higher than experienced by a warhead deployed on a missile, for example (approximately 30,000 Gs for artillery launch versus approximately 20 Gs for a missile system). 
     In some embodiments, the weapon  50  is launched as described herein as a hypervelocity projectile (HVP) to a travel velocity of at least mach 1. 
     Absent adequate provision, these large launch loading forces would tend to axially compress or otherwise deform the warhead  100 , which may damage the warhead and prevent the weapon  50  or the warhead  100  from operating as intended. While the launch load may be countered using a stronger shell  112  or frame system  122 , doing so may add undesirable added weight or impede deployment of the LRPs. Several aspects of the warhead  100  may contribute to enabling the warhead  100  to withstand these artillery launch loads. 
     The warhead  100  addresses this problem by using the LRPs  150  as axial load bearing members or structural supports that reinforce or structurally support the frame system  120  against axial loads (i.e., along axis E-E) on the frame system  120 . That is, the LRPs  150  receive the launch load transferred from the frame system  120  and thereby limit or prevent the frame system  120  from being axially compressed or collapsed by the launch load. Because the LRPs  150  and the frame system  120  support the launch load, the warhead  100  can be constructed such that little or none of the axial launch load is born by the shell  112 , and the shell  112  can therefore be made relatively thin. 
     The performance of the LRPs  150  as launch load bearing members is enabled or enhanced by several aspects of the warhead construction. 
     Because the LRPs  150  are long slender long rods stacked on top of each other, they would ordinarily tend to experience failure due to buckling very easily during launch loading. The shapes of the LRPs  150  and the arrangements of the LRPs  150 , the frame system  120 , and the support inserts  114  serve to prevent or inhibit buckling of the LRPs  150  under axial load so that the LRPs  150  can reliability serve as loaded bearing elements. 
     The warhead  100  uses regular hexagonal-shaped rods  150  because they can pack in a way where each side  164  is touching (and is constrained by) another LRP  150 . This vastly limits each LRP&#39;s  150  ability to sway side to side and cause buckling. 
     Also, the “buckling supports” or support inserts  114  provide more support against buckling. The support inserts  114  accomplish this both by providing face-to-face engagement support between the side faces  164  of the outer LRPs  150  and the conforming inner surface  118  of the support inserts  114 , and by taking up extra space in the bay B. The support inserts  114  may be 3D printed metal structures that attach to the outer casing  112 . 
     The partitions walls  132  and bays B that subdivide each level T 1 -T 5  enable closer packing between the LRPs  150 , and can limit or reduce relative lateral displacement between the LRPs  150 . 
     The frame system  120  distributes the axial launch loading between the frame system  120  and the LRPs  150  themselves. This is accomplished or enhanced by rigidly affixing or connecting all or some of the divider walls  128 ,  129 ,  130  to the central beam  122  and relatively sizing the lengths L 1  of the LRPs  150  and the heights  116  of the levels T 1 -T 5  such that the ends  166  of the LRPs  150  fit snugly against the adjacent walls  128 ,  129 ,  130  or with only very small axial gaps (e.g., no more than 1 mm) between the ends  166  of the LRPs  150  and their adjacent walls  128 ,  129 ,  130 . 
     The reinforcement of the frame system  120  and the warhead  100  by the LRPs  150  may be particularly effective in the case of embodiments (e.g., as illustrated in  FIGS. 4-7 ) wherein the frame system  120  is a multibeam (e.g., tribeam, as shown), unitary member, structure or truss. In these embodiments, the level divider walls  128 ,  129 ,  130  are all rigidly connected to the central beam  122  and the partition walls  132  so that the launch load can be directly transferred from the truss  120  to the LRPs  151 - 155  on each level via the walls  128 ,  129 ,  130 . The unitary truss  120  may also be 3D printed. 
     Warheads according to embodiments of the invention (e.g., the warhead  100 ) may include or provide the following aspects, alternatives and advantages:
         Artillery cannon or gun launched non-hit to kill BMD warhead.   Dispenses long rod penetrators (LRPs) into space and uses energy of the target against itself.   Uses very low ratio of explosive charge to dispensed mass (less than 5%).   Multiple bays to vary the LRP distribution (each bay dispenses at a different velocity since it is mass dependent).   Each bay has a different mass of LRPs—Controlled by varying LRP material and packing pattern   Unlike some other artillery warhead designs that use a very thick aeroshell for structural support, a warhead of the present invention can use a thin aeroshell because the structure loading is handled by the tribeam frame system and the LRPs themselves. The support system of the frame system  120  and the support inserts  114  helps support and distribute loading amongst the rods  150  and away from the thin aeroshell  112 .   In some embodiments, the “tribeam” frame system  120  (including the beam  122 , the level divider walls  130  and the partition walls  132 ) is 3D printed as a unitary member.   In some embodiments, the rods  150  are hexagonal-shaped to improve packing efficiency and improve structural rigidity by limiting space between the LRPs to reduce buckling. In some embodiments, the rods  150  are regular hexagonal-shaped.   Metal buckle supports  114  are added to confine the LRPs  150  against the aeroshell  112  to prevent buckling outward. The supports  114  may be 3D printed.   Rod length may be varied (e.g., in the bays of level T 1  versus the other levels T 2 -T 5 ) to selectively modify the dispense pattern.   Warheads according to embodiments of the invention can use a relatively small amount of HE explosive charge  140  to simply push the rods  150  out into space, and then have the target M fly through the “wall” W of LRPs  150  to do damage, effectively using the kinetic energy of the target M against itself. The warhead can thereby be constructed to have a relatively low C/M ratio (mass of HE explosive/overall mass of warhead ratio) (i.e., a “Low C/M kinetic energy rod warhead”). A low C/M ratio may be very important. Similarly, in some embodiments as described herein wherein the projectile ejection force generator is a an expelling charge or mechanism other than an HE explosive charge, the expelling charge or mechanism can be relatively small in volume and mass, so that the ratio of the mass of the expelling charge or mechanism to the mass of the warhead is relatively low.   The dispense pattern of the LRPs  151 - 155  can be selectively tuned, set, or adjusted using one or more techniques that are conveniently implemented in the inventive design. One such technique is to use different rod material (e.g., a special type of metal in the bays of level T 4  as discussed in the attached) and adjusting the size or amount of HE explosive in level T 1  (i.e., within the bays of level T 1 ) to modify the dispersal pattern to optimize lethality against a given target.       

     As shown, the frame system  120  includes four level divider walls  130  and fifteen partition walls  132 . However, the warhead  120  may include more or fewer level divider walls, partition walls, levels, bays, canisters, and/or projectiles (e.g., LRPs). 
     With reference to  FIGS. 12 and 13 , an alternative construction of the warhead  100  is shown therein as a warhead  200 . The warhead  200  is only shown in fragmentary views showing a frame system  220  and LRPs  251 - 255 . The frame system  220  replaces the frame system  120  in the warhead  100 , and the LRPs  251 - 255  replace the LRPs  151 - 155 , respectively, of the warhead  100 . The remainder of the warhead  200  may be constructed, used, and operated in the same manner as the warhead  100 . 
     The frame system  220  includes a central beam  222 , a front end wall  228 , a rear wall  229 , level divider walls  230 , circumferential partition walls  132 , and bays B corresponding to components  122 ,  128 ,  129 ,  130 ,  132 , and B, respectively. The frame system  220  differs from the frame system  120  in that the bays B of each level T 1 -T 5  of the warhead  200  are angularly offset, rotated, or non-aligned about the central axis E-E with respect to the bays B of one or more of the other levels T 1 -T 5 . For example, in the depicted frame system  220 , the bays B of levels T 1 , T 3  and T 5  are angularly offset from the bays B of the levels T 2  and T 4  by about 60 degrees. 
     The rotationally offset configuration of the bays B may provide certain benefits. This arrangement can better distribute launch loads across the LRPs  251 - 255 . The rotationally offset configuration may increase the structural resistance of the frame system  220  itself due to the mid-span support provided by the tribeam connection of the aft side of each bay divider  232 . 
     The rotationally offset configuration also changes the dispersion pattern of the LRPs  251 - 255 . This can be used to selectively adjust the dispersion pattern to combat different threats (e.g., targets M). 
     As described above, in some embodiments an explosive charge  140  is used as the projectile ejection force generator to generate the ejection force to dispense the LRPs radially outwardly to thereby form a matrix of the LRPs to intersect the target. In some embodiments, the explosive charge  140  is an HE explosive material and the ejection force includes shock waves and gas pressure generated from the detonated HE explosive and directly applied to the projectiles  150  to eject the projectiles. 
     In some embodiments, the explosive charge  140  is a low explosive and the ejection force includes gas pressure generated from the ignited LE explosive (e.g., by deflagration) and directly applied to the projectiles  150  to eject the projectiles. In this case, in some embodiments, the projectiles are not ejected by shock waves generated by the explosive charge  140 . 
     According to further embodiments, other projectile ejection force generators or deployment mechanisms may be used in place of or in addition to the explosive charge  140 . 
     In some embodiments, the explosive charge  140  is omitted and the projectile ejection force generator is a gas generator that rapidly generates a pressurized gas that pushes the projectiles  150  out. In some embodiments, this pressurized gas acts directly on the projectiles. In some embodiments, the gas generator is a non-explosive gas generator. In some embodiments, the gas generator is installed in the central cavity  124 . 
     In some embodiments, the explosive charge  140  is omitted and the projectile ejection force generator includes an expelling system including a gas generator in combination with one or more airbags. In this case, the gas generator may be installed in the central cavity  124  and used to inflate the one or more airbags in the bays B. The inflating airbag(s) will push the LRPs  150  radially outward into space. In some embodiments, the LRPs  150  are attached to (e.g., sewn into) the airbag itself to maintain proper alignment of the LRPs  150  during dispersion. 
     In some embodiments, the explosive charge  140  is omitted and the projectile ejection force generator is a spring-force system. The spring-force system may include a loaded spring (e.g., a compressed spring) and a release mechanism. When the spring is released, the spring force pushes the LRPs  150  radially outward into space. 
     As discussed above, it is contemplated that weapons including a warhead as disclosed herein can also be deployed using mechanisms other than artillery. 
     Many alterations and modifications may be made by those having ordinary skill in the art, given the benefit of present disclosure, without departing from the spirit and scope of the invention. Therefore, it must be understood that the illustrated embodiments have been set forth only for the purposes of example, and that it should not be taken as limiting the invention as defined by the following claims. The following claims, therefore, are to be read to include not only the combination of elements which are literally set forth but all equivalent elements for performing substantially the same function in substantially the same way to obtain substantially the same result. The claims are thus to be understood to include what is specifically illustrated and described above, what is conceptually equivalent, and also what incorporates the essential idea of the invention.