Abstract:
A mission responsive ordnance of the present invention arranges a plurality of projectiles in a bundled configuration. The bundled configuration is defined by the projectiles and a bundling means which, together, form a combination that bears loads generated when the bundled configuration strikes and penetrates a target. Unbundling means, coupled to the bundling means, can be operated to selectively render the bundling means inoperative before the target is struck so that one or more of the projectiles are released from their bundled configuration.

Description:
ORIGIN OF THE INVENTION  
       [0001] The invention described herein was made in the performance of official duties by employees of the Department of the Navy and may be manufactured, used, licensed by or for the Government for any governmental purpose without payment of any royalties thereon. 
     
    
     
       FIELD OF THE INVENTION  
         [0002]    The invention relates generally to ordnance, and more particularly to ordnance that can be adapted to a variety of missions after the ordnance has been launched.  
         BACKGROUND OF THE INVENTION  
         [0003]    Historically, strike and support weapons have been designed to kill a specific target class such as hard point targets (e.g., power plants, aircraft shelters, etc.) using kill mechanisms or employment techniques that have very limited effectiveness against other types of target classes to include distributed area and armored targets. As the number of target classes has increased, so has the number of different ordnance payloads. Over time, this has resulted in the development of numerous specialized weapons, some of which require different launch platforms.  
           [0004]    In addition to target evolution, recent conflicts have emphasized the need to achieve operation objectives with a minimum impact to the surrounding area. Tactical situations requiring the complete destruction of targets are becoming less and less frequent. Rather, the trend is toward a measured response. For example, in many cases, forces are moving through a hostile area so rapidly that it is only necessary to neutralize the threat and not destroy the area&#39;s infrastructure (e.g., roads, bridges, power sources, etc.) that primarily benefits an innocent population. Furthermore, there are the issues associated with friendly, dud sub munitions left in the area. Still, in other cases, it is necessary to disable an area by shutting down a infrastructure for a specified period of time. In this scenario, a measured amount of damage must be brought to bear on a precise pressure point such as a single generator in a power plant or a power distribution switching station. If too much of the power plant is destroyed, an excessive shut down would occur and the strategic objective would not be met. In still other scenarios, the presence of civilians, hospitals or historic/religious sites in close proximity to the intended target means that collateral damage must be minimized. Lastly, the neutralization of sites containing weapons of mass destruction presents a most formidable challenge. Too much damage could cause a release of lethal chemicals/agents into an area inhabited by innocent civilians or even one&#39;s own troops.  
           [0005]    All of the above-described scenarios call for a weapon that can deliver a measured lethal dose with sufficient precision to kill only the intended target(s). At the same time, large targets that must be totally destroyed will always exist. These targets call for large, non-nuclear payloads, most of which are delivered by cruise missiles or manned aircraft. Thus, future war fighting needs must focus on the ability to defeat various size targets with various levels of attack strength. In all cases, target destruction with minimal collateral damage demands that the ordnance penetrate its target prior to destruction.  
           [0006]    The above-described goals of the various war fighting scenarios require a new class of ordnance with the ability to adapt to different types of attacks and different magnitudes of attack strength in response to the key vulnerabilities of a particular target. Such a mission responsive ordnance would reduce the need for target specific weapons and would provide a more robust ordnance capability not easily outdated by target evolution or modifications to tactics.  
         SUMMARY OF THE INVENTION  
         [0007]    Accordingly, it is an object of the present invention to provide a mission responsive ordnance.  
           [0008]    Another object of the present invention is to provide a mission responsive ordnance that can be adapted to different kinds of attacks.  
           [0009]    Yet another object of the present invention is to provide a mission responsive ordnance that can be adapted to different magnitudes of attack strength.  
           [0010]    Still another object of the present invention is to provide a mission responsive ordnance designed to penetrate its target in each of its attack modes.  
           [0011]    A still further object of the present invention is to provide a mission responsive ordnance that can operate in either a unitary or subdivided-munitions mode.  
           [0012]    Yet another object of the present invention is to provide a mission responsive ordnance that can be delivered to its destination using current launch technology.  
           [0013]    Other objects and advantages of the present invention will become more obvious hereinafter in the specification and drawings.  
           [0014]    In accordance with the present invention, a mission responsive ordnance includes a plurality of projectiles arranged in a bundled configuration. First bundling means are provided for maintaining the bundled configuration such that the first means and at least a first portion of the projectiles are coupled together to form a combination that bears penetration and deceleration loads generated when the bundled configuration strikes and penetrates a target. Second unbindling means are coupled to at least one of i) the first bundling means and ii) at least a second portion of the projectiles for selectively releasing the second portion of projectiles from the bundled configuration before striking the target.  
           [0015]    In a particular embodiment of the present invention, the bundled configuration is maintained by a nose cone assembly, a frangible tubular body and an aft support. The nose cone assembly is located forward of the projectiles and has rearward-facing sockets for capturing therein in a complementary fashion portions of each nose of the projectiles. The frangible tubular body has a forward end coupled to the nose cone assembly and encases the projectiles in their bundled configuration. The aft support is coupled to the aft end of the frangible tubular body. Similar to the nose cone assembly, the aft support has forward-facing sockets for capturing therein in a complementary fashion portions of each of the projectile&#39;s tails. The combination of nose cone assembly, frangible tubular body and aft support restricts axial, radial and lateral movement of the projectiles in their bundled configuration. Further, the nose cone assembly, aft support and projectiles bear penetration and deceleration loads generated when the embodiment is operating in a unitary munitions mode. The embodiment could alternatively be operated in a sub-divided munitions mode by fracturing the frangible tubular body before the target is struck. In this mode, some or all of the projectiles are released from their bundled configuration and allowed to disperse to strike a variety of dispersed targets. 
       
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0016]    [0016]FIG. 1 is a longitudinal cross-sectional view of one embodiment of a mission responsive ordnance in accordance with the present invention;  
         [0017]    [0017]FIG. 2 is an axial cross-sectional view of the mission responsive ordnance taken along line  2 - 2  in FIG. 1;  
         [0018]    [0018]FIG. 3 is an axial cross-sectional view of another mission responsive ordnance in which a core projectile remains with the originally-launched ordnance while peripheral projectiles are released therefrom when the ordnance is used in a subdivided mode;  
         [0019]    [0019]FIG. 4 is an isolated cross-sectional view of a nose cone having a blunt tip and have pointed sockets for receiving pointed nose cones of projectiles captured by the nose cone;  
         [0020]    [0020]FIG. 5 is an axial cross-sectional view of another embodiment of the present invention in which axially-extending stiffening webs couple the core projectile to the mission responsive ordnance&#39;s outer body;  
         [0021]    [0021]FIG. 6 is an axial cross-sectional view of another embodiment of the present invention in which a longitudinally-fluted core projectile supports peripheral projectiles and means for expelling each peripheral projectile at time of release;  
         [0022]    [0022]FIG. 7 is an axial cross-sectional view of still another embodiment of the present invention in which the projectiles are housed within individual launch tube&#39;s;  
         [0023]    [0023]FIG. 8 is a side cross-sectional view of still another embodiment of the present invention in which the projectiles housed by the mission responsive ordnance are wedge-shaped;  
         [0024]    [0024]FIG. 9 is a side view of another embodiment of the present invention in which a solid projectile section is geometrically subdividable;  
         [0025]    [0025]FIG. 10 is a cross-sectional view taken along line  10 - 10  in FIG. 9;  
         [0026]    [0026]FIG. 11 is a side view of another embodiment of the present invention in which the mission responsive ordnance is entirely subdividable into its geometric constituents; and  
         [0027]    [0027]FIG. 12 is cross-sectional view taken along line  12 - 12  in FIG. 11. 
     
    
     DETAILED DESCRIPTION OF THE INVENTION  
       [0028]    Referring now to the drawings, and more particularly to FIG. 1, an embodiment of a mission responsive ordnance (MRO) in accordance with the present invention is shown and referenced generally by numeral  10 . Although not a requirement or limitation of the present invention, MRO  10  would typically have a delivery vehicle (not shown) coupled to its aft end. Such a delivery vehicle could include a propulsion mechanism, control surfaces, and guidance and control mechanisms such as those used on short or long-range missiles. Further, although MRO  10  will be described herein relative to an airborne ordnance, it is to be understood that the inventive principles of the present invention could also be applied in an underwater environment.  
         [0029]    At its forward end, MRO  10  has a nose cone  12  designed to penetrate a target when MRO  10  is called upon to act as a unitary ordnance as will be explained further below. As is understood in the art of penetrating ordnance, nose cone  12  can be hollow as shown although this is not a limitation of the present invention. Further, although nose cone  12  has a pointed tip  12 A, it could also have a blunt tip to minimize ricochet as is understood in the art.  
         [0030]    The aft end of nose cone  12  is configured with a plurality of sockets  12 B that face axially rearward from nose cone  12 . Each of sockets  12 B is sized and shaped to receive, in a complementary fashion, at least a portion of the nose of each of a plurality of projectiles  14  which are illustrated in a side view. The portion of projectiles  14  received in sockets  12 B could be mechanically/chemically fuzed/bonded to sockets  12 B such that the mechanical/chemical fuze/bond can be broken or eliminated when MRO  10  is to be used in its subdivided munitions mode.  
         [0031]    Each of projectiles  14  is capable of striking and penetrating a target. In general, each of projectiles  14  includes a nose cone  14 A at its forward end and a rigid body section  14 B coupled to nose cone  14 A and extending to an aft end  14 C which can be attached to or integrated with rigid body section  14 B. Nose cone  14 A can have a blunt tip (as shown) or a pointed tip without departing from the scope of the present invention. Furthermore, any and/or all of projectiles  14  can include an explosive payload, the choice of which is not a limitation of the present invention.  
         [0032]    In accordance with the present invention, any and/or all of projectiles  14  also function as a structural component of MRO  10  when MRO  10  is to be utilized as a unitary ordnance. That is, projectiles  14  must withstand strike, penetration and deceleration loads generated when MRO  10  strikes/penetrates a target in its unitary ordnance mode. Accordingly, those of projectiles  14  serving this function must be capable of coupling the deceleration load (passed from nose cone  12 ) to adjacent projectiles and/or adjacent structural elements. This can be achieved through various physical locking or interlocking mechanisms, or by physically capturing the projectiles between forward and aft components. A physical lock can take the form of fuzed or bonded structural elements where the bond is subsequently broken via mechanical, electrical or chemical means. If interlocking of mechanical parts is used, the interlock can be subsequently released by mechanical, electrical or chemical means. Physical capture of the projectiles can be achieved with axial, lateral and radial capture mechanisms. Various non-limiting examples will be described herein.  
         [0033]    One example of a capture mechanism is illustrated in the FIG. 1 embodiment. The forward part of the capture mechanism includes nose cone  12  described above. Located aft of projectiles  14  is an aft support  16  configured with a plurality of sockets  16 A that face axially forward towards nose cone  12 . Each of sockets  16 A is sized and shaped to receive, in a complementary fashion, at least a portion of each aft end  14 C of projectiles  14 . Thus, nose cone  12  and aft support  16  position, align and capture projectiles  14  laterally and longitudinally in a bundled configuration. The portion of projectiles  14  received in sockets  16 A could be mechanically/chemically fuzed/bonded to sockets  16 A such that the mechanical/chemical fuze/bond can be broken or eliminated when MRO  10  is to be used in its sub-divided munitions mode.  
         [0034]    Physical coupling of nose cone  12  to aft support  16  is accomplished in the illustrated embodiment by a tubular body  18  that essentially encases and radially restrains projectiles  14  in their bundled configuration. Further, the combination of nose cone  12 , tubular body  18  and aft support  16  prevents axial movement of projectiles  14  until or unless it is desired for some or all of projectiles  14  to fly free of MRO  10  and act as individual projectiles. Absent the release of projectiles  14 , nose cone  12 , projectiles  14  and aft support  16  form an integral structural element of MRO  10  operating in its unitary mode.  
         [0035]    To take advantage of the sub-divided munitions mode of MRO  10 , tubular body  18  must be eliminated or removed during flight of MRO  10 . One way of facilitating removal of tubular body  18  during flight is to make tubular body  18  a frangible structure that breaks apart at a selected time during the flight of MRO  10 . Thus, tubular body  18  could be a pre-scored metal or composite structure that fractures in a pre-defined fashion. Such fracturing could be brought about by a fracture initiation charge  20  coupled to, for example, positions along (or about) tubular body  18 . Charges  20  could be initiated at a predetermined time/sequence after launch, by means of a radio wave signal, or by other means known in the art. Once tubular body  18  fractures, nose cone  12  and aft support  16  fall away so that projectiles  14  disperse in the air from the bundled configuration. Note that if projectiles  14  are fuzed/bonded into sockets  12 B and/or sockets  16 A, the fuze/bond must be broken before nose cone  12  and aft support  16  can fall away.  
         [0036]    The particular bundled configuration of projectiles  14  is not a limitation of the present invention. However, by way of example, projectiles  14  can be arranged as shown in FIG. 2 with a centrally-positioned core projectile  14 - 1  and a number of peripheral projectiles  14 - 2  radially surrounding centrally-positioned core projectile  14 - 1 . The number and/or size of core projectile  14 - 1  and peripheral projectiles  14 - 2  are not limitations of the present invention. That is, the core and peripheral projectiles can be the same size or different sizes. Still further, the bundled configuration of projectiles  14  is not limited to a core/peripheral projectile geometry. For example, if three projectiles  14  of equal diameter are used, there would be no core projectile as they could be arranged in a triangular geometry.  
         [0037]    In operation, MRO  10  is launched into the air toward specified target(s). If MRO  10  is to be used in its unitary mode, fracture charge  20  could be removed or inactivated prior to or during launch. Upon impact with a target, nose cone  12  transfers impact, and subsequent penetration and deceleration loads, along projectiles  14  and on to aft support  16  as described above. If, however, MRO  10  is to be used in a subdivided mode, some or all of projectiles  14  are released into the air at a prescribed time during flight as described above. The released ones of projectiles  14  then disperse to cover a broader area of targets. Although not shown, each of projectiles  14  released from MRO  10  can be “smart” projectile in operating under control of its own guidance/control mechanisms.  
         [0038]    While MRO  10  can be configured to release all of projectiles  14  in a subdivided mode, this need not be the case. For example, as illustrated in FIG. 3, core projectile  14 - 1  could be surrounded by a rigid frame such as rods  22  that rigidly couple the nose cone (not shown) to the aft support (not shown). In this example, when used in the subdivided mode, core projectile  14 - 1  would remain integral with the nose cone and aft support while peripheral projectiles  14 - 2  were released therefrom. (Note that it may be necessary to have the fracturing charge further coupled to the outer periphery of the nose cone of the MRO in order to allow for the radial and/or lateral release of peripheral projectiles  14 - 2 .) Rods  22  would restrain core projectile  14 - 1  from release and further aid in withstanding strike and penetration forces whether the MRO is used in the unitary or subdivided mode.  
         [0039]    Variations on the present invention&#39;s mission responsive ordnance approach can be implemented without departing from the scope of the present invention. A number of such variations will be presented herein by way of example. However, it is to be understood that these examples do not represent an exhaustive set of such variations.  
         [0040]    With respect to the nose cone of the MRO, it can have a pointed tip as in nose cone  12  or it can have a blunt tip  13 A as illustrated in the isolated view of nose cone  13  shown in FIG. 4. Further, as mentioned above, the projectiles captured by the nose cone can have a blunt tip (as evidenced in FIG. 1) or can have a pointed tip. In the case of pointed tip projectiles, sockets  13 B are pointed and sized in a complementary fashion to the projectiles (not shown) they are to receive.  
         [0041]    Other variations in the present invention relate to the structure used to maintain and/or release the bundled configuration of the projectiles while the MRO is operating in its unitary mode. For example, rather than using a fracturing charge  20  coupled to the exterior of frangible tubular body  18  as described above for MRO  10 , the present invention could utilize internally-mounted fracture charges. More specifically, as illustrated in FIG. 5, axially extending stiffening webs  24  can be coupled to core projectile  14 - 1  and extend radially out to tubular body  18 . Stiffening webs  24  can be captured in the MRO&#39;s nose cone and aft support, neither of which is illustrated in this view. A fracture charge  26  could be mounted on and along the outboard-end of each web  24 . In this embodiment, webs  24  aid in withstanding strike/penetration loads when the MRO is operating in the unitary mode. When the MRO is operating in a subdividing mode, webs  24  serve to position charges  26  and can aid in the directing of peripheral projectiles  14 - 2  when they are released.  
         [0042]    Another variation of the present invention is illustrated in FIG. 6 where core projectile  34 - 1  has its outer body longitudinally fluted to receive peripheral projectiles  34 - 2 . Each peripheral projectile  34 - 2  is fuzed to core projectile  34 - 1  along fuzed joints  36  running the length of the projectiles. In this embodiment, axially-extending expelling charges  38  are positioned radially inward from fused joints  36 . The fluting of core projectile  34 - 1  is such that a gap  40  is formed between each pair of charges  38 . If peripheral projectiles  34 - 2  are to be released, charges  38  are initiated with resulting gases expanding into gap  40 . The pressure in gap  40  builds until fuzed joints  36  fail. At this point, the gases act to propel/expel peripheral projectiles  34 - 2  radially outward.  
         [0043]    Still another variation of the present invention is illustrated in FIG. 7 where any and/or all of projectiles  14  (e.g., core projectile  14 - 1  and peripheral projectiles  14 - 2 ) are housed within individual launch tube&#39;s  50 . Upon fracture of tubular body  18 , launch tube&#39;s  50  with their housed projectiles are dispersed from the MRO with each launch tube  50  subsequently launching its projectile. The particular choice of launch tube and associated launch mechanism is not part of or a limitation of the present invention and will, therefore, not be described further herein.  
         [0044]    Other variations of the present invention relate to the geometry of the projectiles housed by the MRO. For example, as illustrated by MRO  60  in FIG. 8, each of projectiles  64 - 1 ,  64 - 2  and  64 - 3  define wedge-shaped external geometries. In their bundled configuration, adjacent wedge-shaped projectiles alternate with respect to their direction of taper. That is, for the illustrated example, the tapered end of projectile  64 - 1  is at the forward end of MRO  60 , the tapered end of projectile  64 - 2  is at the aft end of MRO  60  and the tapered end of projectile  64 - 3  is at the forward end of MRO  60 . In this way, when MRO  60  is to be used in a unitary mode, strike/penetration loads cause projectiles  641 ,  64 - 2  and  64 - 3  to lock together.  
         [0045]    Another approach to the mission responsive ordnance of the present invention will now be described with the aid of the side view of FIG. 9 and the cross-sectional view of FIG. 10. In FIG. 9, MRO  70  has a penetrating nose cone  72  with a solid cylindrical projectile section  74  coupled thereto. Projectile section  74  comprises a geometrically sub-dividable arrangement of individual projectiles. For example, as illustrated in FIG. 10, a cylindrical core projectile  74 - 1  is surrounded by arc-shaped peripheral projectiles  74 - 2 . Note that the number of peripheral projectiles  74 - 2  can be fewer or greater in number than that shown. The coupling and uncoupling of the projectiles to/from one another and to/from nose cone  72  can be accomplished by means of fuzed joints  76  and expelling charges  78 . Gaps  79  between charges  78  are provided to allow gases from initiated charges  78  to build therein until pressure is sufficient to bring about failure of fuzed joints  76 . As with one of the previously-described embodiments, core projectile  74 - 1  could also be configured to remain with nose cone  72  at all times.  
         [0046]    The approach illustrated by MRO  70  could be further extended to MRO  80  illustrated in FIGS. 11 and 12. More specifically, the entirety of MRO  80  is constructed as a solid projectile with each section thereof forming a geometric portion thereof. In the illustrated example, MRO  80  is dividable longitudinally into four sections with each section  84 - 1 ,  84 - 2 ,  84 - 3  and  84 - 4  forming a portion of the nose and body of MRO  80 . Coupling and uncoupling of projectile sections could once again be accomplished by means of fuzed joints  86  and a longitudinally extending fracture/expelling charge  88 . The gases from charge  88  expands into gaps  90  until joints  86  fail. Note that the size of charge  88  and gaps  90  are exaggerated for purpose of illustration.  
         [0047]    The advantages of the present invention are numerous. Recent conflicts have strongly suggested the need for a new form of ordnance that can address the wide spectrum of surface targets and target scenarios that are present around the globe. These scenarios present fixed hard targets as well as mobile and area targets which can be embedded in highly vulnerable civilian settings. This creates a demand for weapons that can deliver a large punch against large hard targets, multiple smaller punches against smaller area targets and light taps against some special targets in highly vulnerable surroundings. The mission responsive ordnance of the present invention offers this capability through the use of novel ordnance configurations that can perform in different modes. In the unitary mode, the ordnance section remains whole to defeat single, large targets (e.g., power plants, communications centers, etc.). In a subwarhead mode, the unitary ordnance section splits into multiple smaller subwarheads that can independently seek smaller ground targets (e.g., missile launchers, radar sites, artillery gun and crew). The choice of mode can be made prior to launch or while the ordnance is enroute.  
         [0048]    The multiplicity of options represents a significant shift in conventional strike warfare. It addresses the change in war fighting tactics, the evolving diversity of targeted threats and the need to outfit an arsenal having more firepower for fewer dollars of expenditure. The concepts presented herein indicate potential for high payoffs in war fighting capability given specific investments in the ordnance technology base. Analysis against current threat targets indicates a 40 to 80 percent reduction in sorties required for target destruction as compared with current cruise missiles.  
         [0049]    In summary, specific benefits of the present invention include increased effectiveness against a broad set of targets, reduction of weapon types through mission consolidation, ability to focus kill mechanisms on the most vulnerable point of specific targets, the ability to minimize collateral damage and the ability to defeat multiple targets. The potential for growth in capability is tremendous given development of additional technologies.  
         [0050]    Although the invention has been described relative to a specific embodiment thereof, there are numerous variations and modifications that will be readily apparent to those skilled in the art in light of the above teachings. It is therefore to be understood that, within the scope of the appended claims, the invention may be practiced other than as specifically described.