|Publication number||US3818833 A|
|Publication date||Jun 25, 1974|
|Filing date||Aug 18, 1972|
|Priority date||Aug 18, 1972|
|Also published as||DE2340653A1|
|Publication number||US 3818833 A, US 3818833A, US-A-3818833, US3818833 A, US3818833A|
|Original Assignee||Fmc Corp|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (7), Referenced by (65), Classifications (19)|
|External Links: USPTO, USPTO Assignment, Espacenet|
[ June 25, 1974 INDEPENDENT MULTIPLE HEAD FORWARD FIRING SYSTEM  Inventor: Guy C. Throner, Jr., Saratoga,
 Assignee: FMC Corporation, San Jose, Calif.
3,388,664 6/1968 Kelly et a1 102/4 3,500,714 3/1970 Cullinane 89/1 R 3,646,888 3/1972 Posson et a1. 89/1 R Primary ExaminerSamuel W. Engle Attorney, Agent, or Firm-A. J. Moore; C. E. Tripp [5 7] ABSTRACT A missile carries a plurality of independent explosive heads which when fired direct fragments only in a forward direction. The missile releases all heads either in response to a timed delay from drop or launch or in response to movement of the missile to a predetermined position relative to the target. Upon release the explosive heads are rotated to swing each head away from the other heads while retaining orientation of each head so that firing of the dispersed heads will cause fragments to discharge forwardly toward the target without undue interference with the fragments from other heads.
8 Claims, 16 Drawing Figures fi m-FEW PAIENIED JUNZSIBH SHEET 1 BF 6 PATENTEDJUNZSISIII v SHEU 3 0F 6 FIG E PATENTEBJUN25I974 818,833
SHEET 6 (1F 6 TIE ll TIE ,12
INDEPENDENT MULTIPLE HEAD FORWARD FIRING SYSTEM- CROSS REFERENCE TO RELATED APPLICATIONS The independent multiple head forward firing system of the present invention is related to an application Ser. No. 281,878 by James F. Cullinane et al filed on even date herewith and assigned to the assignee of the present invention.
BACKGROUND OF THE INVENTION 1. Field of the Invention This invention pertains to anti-personnel and antimaterial weapons and more particularly relates to a forward firing explosive head, and a missile that carries a plurality of independent forward firing explosive heads and means for dispersing the heads.
2. Description of the Prior Art Fragmentary anti-personnel and anti-material explosive heads are known which when exploded propel fragments at high velocity against the target. However, the known fragmentation heads of this type not only propel fragments at the target but also propel other fragments away from the target. U.S. Pat. No. 3,500,714 which issued to Cullinane on Mar. 17, I970 and is assigned to the assignee of the present invention discloses a system for spinning explosive heads which is similar to that used in certain embodiments of the present invention.
SUMMARY OF THE INVENTION The multiple head forward firing system of the present invention provides a fragmentary explosive head which when fired propels the fragments only in a forward direction toward the target. A plurality of these heads are preferably carried by a missile, such as an aerial bomb, projectile, or guided missile; and the missile releases each head either after a predetermined interval from launching or when in range of the target for tangential separation from each other while retaining their aimed orientation so that the fragments of one head will not interfere with fragments fired from other ones of the heads, and so that a wide target area will be contacted by the fragments of these several heads.
It is, therefore, one object of the present invention to provide an explosive head having a fragmentary wall only on the forward end of the head for directional control of the fragment upon firing of the head.
Another object is to provide a relatively light explosive head by providing a fragmentation wall only on the forward end of the head.
Another object is to provide a missile having a plurality of forward firing heads therein with the heads retaining their directional orientation and with each head being swung radially outward from the missile when in the proximity of the target and prior to firing the heads.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective of a missile containing a plurality of forward firing heads therein, the missile'being illustrated as an aerial bomb substantially as it would appear when on the bomb racks of an aircraft.
FIG. 1A is a diagrammatic perspective with parts in section illustrating the manner in which the forward firing heads are stacked together.
FIG. 1B is a diagrammatic perspective of a missile illustrating first means for rotating the missile for dispersing the explosive heads, certain parts being cut away.
FIG. 1C is a diagrammatic side elevation illustrating second means for rotating the missile, certain parts being cut away.
FIG. 1D is a side elevation similar to FIG. 1C illustrating third means for rotating the missile, certain parts being cut away.
FIG. 2 is a diagrammatic perspective illustrating the missile after a fuze has ignited cutting charges which have separated the nose cone from the body of the missile and has longitudinally severed the missile body into three sections, the plurality of forward firing heads being shown as they appear after being spun out of the open missile body.
FIG. 3 is a diagrammatic perspective illustrating the wide firing pattern of the plurality of forward firing heads as the heads approach the targets, the firing elevation being illustrated in greatly foreshortened scale.
FIG. 4 is an enlarged diagrammatic central section taken through one of the explosive heads.
FIG. 5 is a diagrammatic perspective similar to FIG. 2 but illustrating a plurality of forward firing heads of a second embodiment of the invention immediately after they have been released from the missile, each head being fired by a proximity fuze.
FIG. 6 is a diagrammatic perspective illustrating the firing pattern of the heads of FIG. 5.
FIG. 7 is an enlarged diagrammatic central section taken through one of the forward firing heads of FIG. 5 when the head is in its compact position.
FIG. 8 is a section similar to FIG. 7 but illustrating the parts in an expanded position.
FIG. 9 is a diagrammatic perspective similar to FIG. 2 but illustrating a plurality of forward firing heads of a third embodiment of the invention.
FIG. 10 is a diagrammatic perspective illustrating the firing pattern of the heads of FIG. 9.
FIG. 11 is an enlarged diagrammatic central section taken through one of the forward firing heads of FIG. 9 when the head is in its compact position.
FIG. 12 is a section similar to FIG. 11 but illustratingthe parts in their expanded positions.
DESCRIPTION OF THE PREFERRED EMBODIMENT The forward firing system 20 (FIGS. 14) of the first embodiment of the invention is illustrated as a missile in the form of an aerial bomb 22 having a plurality of independent forward firing heads M therein. It will be understood, however, that other types of missiles, such as mortar shells, rockets, or anti-aircraft shells may be used to transport or launch the forward firing heads toward their targets.
In the illustrated first embodiment of the invention, the missile or bomb 22 (FIG. I) comprises a thin walled tubular body 26, a nose cone 28 on one end of the body with a time fuze or proximity fuze 2'9 therein, and a tail assembly 30 on the other end with direction controlling fins 32 pivotally mounted thereon all as is well known in the art.
The forward firing heads 24 are in the shape of circular discs each having a cylindrical wall 34 (FIG. 4) of plastic or thin metal with a lower flange 36 and a rear flat wall 38. A lower or forward fragmentation wall 40 made. up of one or more layers 42 and 44 of metal fragments 46 such as steel, is supported by the lower flange 36. A fragmenting plate may be substituted for the pre cut fragmentation wall 40 if desired. The fragments 46 are normally interconnected with sufficient strength to define the wall 40 but separate into individual fragments 46 upon firing of an explosive charge 48. The explosive charge 48 is illustrated as including a wave shaper 50, and is fired by a fuze 52 such as a time delay sub-missile fuze.
The plurality of heads 24 are concentrically stacked in the tubular body 26 in abutting contact with each other as illustrated in FIG. 1B, 1C and 1D, and with the fragmentation wall 40 of each head facing the nose cone 28 (FIG. 1). The fuze 29 is provided in order to open the body 26 at a. predetermined time from launch or at the desired distance from the target. If the fuze is a proximity] fuze, it may be adjusted to fire when the missile is at any one of a plurality of predetermined distances from the target. The fuze 29 (FIG. l)'is connected to an annular cutting charge 54 on the internal surface of the body adjacent the nose cone 28, and is also connected to three linear cutting charges 56 (only one being illustrated in FIG. I) placed at even intervals on the inner or outer surface of the body 26 and extending longitudinally thereof for substantially the full length of the body. Activation of the fuze 29 fires the cutting charges 54 and 56 thus severing the nose cone 28 from the body 26 and longitudinally cutting the body into three pieces 58 (only two being shown in FIG. 2). The wind resistance immediately strips the nose cone from the missile and peels the three body strips 58 therefrom as indicated in FIG. 2 leaving the stack of forward firing heads 24 exposed for substantial tangential dispersal.
In order to disperse the several forward firing heads 24, and retain orientation of each head with its fragmentation wall 40 directed toward the target, each missile is first spun as a unit thus imparting rotation to each forward firing head about its longitudinal axis prior to activationof the cutting charges 54 and 56.
FIGS. 13, IC and 1D illustrate three separate ways of rotating at least the load carrying portions of the missiles about their longitudinal axes. In FIG. 1B, the tail assembly 30b is rigid with the body 26b of the missile 22b and has its fins 32b angled relative to the missiles longitudinal axis thus causing air resistance to spinthe entire missile. In FIG. IC, the tail assembly 300 is rigid with the body 26c of the missile 22c is spun by a rotating motor 600 which is illustrated as a rocket propelled device having several substantially tangential rocket motors 610 which communicate with openings (not shown) in the missile body 260 thus rotating the entire missile when activated. FIG. 1D illustrates a missile spinning system that is similar to the missile 22c except that the tail assembly 30d is journaled on the body 26d andaccordingly does not spin with the body when the motor 60d is activated.
As best illustrated in FIGS. 1A and 1D, the forward firing heads 24,24d in the missile are interconnected to each other and to the head rotating motor 60,60d by pins 62,62d. The heads 24,24d are releasably connected to the next adjacent head or to the motor 60,60d by one of the pins 62,62d, (FIG. 1A). Each pin 62,62d is secured to one of the heads 24,24d (or the motor 60) adjacent its periphery and is slidably received in a radial edge slot 64,64d in the adjacent wall of the next adjacent head in a mannersimilar to that disclosed in the aforementioned Cullinane patent. Thus, the motor 60,60d causes all of the heads to rotate as a unit with the end head or heads of the stack of heads being the first to be spun from the stack of heads. The remaining plurality of heads will each progressively peel off the ends of the stack of heads and will be tangentially dispersed as indicated in FIG. 2. The gyroscopic affect of each spinning head will maintain orientation of the head with the fragmentation wall 40 facing the target.
In operation of the first embodiment of the invention, an aerial bomb or missile 22 loaded with a stack of forward firing heads 24 therein is dropped from an aircraft. The fuze 29 is activated in response to the bomb reaching a predetermined elevation above the target; or alternately, in response to a predetermined interval of time elasping from the time of drop, depends upon what type of fuze is being used. The activation of the fuze 29 preferably occurs when the bomb is within between about 5,000 to 200 feet from the target area. If the bomb is of the type illustrated in FIGS. 1C or 1D, activation of the fuze 29 first fires the motor 60c, 60d for a period of about 1/10 to 2 seconds thereby spinning the missile. After a delay of about I/ to 2 seconds, a delayed signal from the fuze ignites the cutting charges 54 and 56 allowing air resistance to peel the nose cone 28 and body strips 58 from the stack of forward firing heads 24. The rotating heads 24 then disperse outwardly as indicated in FIG. 2 before the time delay sub-missile fuzes 52 (FIG. 4) fire their respective heads 24. The fuses 52 fire after a preset delay after dispersion'of about l/ 100 to 10 seconds. The fired explosives 48 and 50 in each head breaks the fragmentation wall 40 into a plurality of separate fragments 46. Subsequently all of the fragments 46 are thus propelled in a generally conical pattern toward the target as illustrated in FIG. 3.
Although the size of the missile is not controlling, an effective missile size may be within the range of about 4 to 60 inches in diameter, and an effective fragment size may be about 10-1 ,000 grains.
The forward firing system 20' of the second embodiment of the invention illustrated in FIGS. 5-8 is fired, and the heads 24' are dispensed in a manner substantially the same as that of the first embodiment of the invention. The system 20' differs only in the particular type and shape of forward firing head 24' being used. Accordingly, only the heads 24' will be described in detail and parts which are similar to those described in the first embodiment of the invention will be assigned the same numerals followed by a prime When the heads 24' are stacked in the bomb 22' they are in their compacted positions as illustrated in FIG. 7, and after the heads 24' have been rotated and dispersed from the bomb they expand to the position illustrated in FIGS. 5 and 8. A jet motor or angled vanes 32' in the tail assembly 30 may be used to spin the head as in the first embodiment of the invention and serve to disperse the several forward firing heads as diagrammatically illustrated in FIGS. 5 and 6.
Each forward firing head 24' comprises a relatively thin plastic or metal, generally disc shaped shell 86 (FIGS. 7 and 8). The shell 86 includes a cylindrical side wall 88 having an outwardly bowed concave lower wall 90 and an outwardly bowed concave upper wall 92. A concave fragmentation wall 94 made up of fragments 96 within the shell 86 bears against the lower wall and has an explosive charge 98 and a wave shaper 100 thereabove. It is to be understood that the wave shaper is optional. A proximity fuze 102 which includes a pri mary reflector or antenna 106, a booster 103, and a wave generator is provided for each head 24. The reflector or antenna 106 is mounted on the free end of an expandible helical leaf spring 108 (FIG. 8) which fits within a housing 109 secured in a small cavity in the lower wall 90 when compacted as illustrated in FIG. 7. The antenna 106 is projected outwardly a substantial distance from the forward wall 90 as illustrated in FIG. 8 in response to the next forward head 24 moving away from the wall 90. The leaf spring 108 may be of the type disclosed in US. Pat. No. 3,587,658 which issued to Charles M. Giltner on June 28, 1971.
As indicated in FIG. 8, the antenna or reflector 106 directs electrical wave signals against a multi-leafed parabolic secondary reflector 110 for reflection to the target area. The reflector 110 thereafter collects waves reflected off the target and target area, and focuses all such return signals at the apex of the concave reflector or antenna until the set distance is ascertained by the fuze which then detonates the explosive 98.
The secondary reflector 110 is composed of a plurality of resilient pie shaped leafs 112 having their inner ends secured to the outer periphery of the housing 109 and having their outer ends engaging a ring 114 slidably received on the outer periphery of the side wall 88 of the shell 86. A helical spring 116 is disposed between the slidable ring 114 and a stationary ring 118 that is rigidly secured to the cylindrical side wall 88. As indicated in FIG. 7, each pin 62' of the spinning mechanism is secured to a hub 119 on the ring 114 of one head 24 and is slidably received in an edge slot 120 in the stationary ring 118 of the next adjacent head 24. When the pins 62 have been removed from their associated slots 120 by swinging the heads 24 in the stack away from their stacked position as previously described, the reflector 106 and the secondary reflector 110 of the next above head 24' are free to extend under the influence of the helical leaf spring 108 and the helical spring 116, respectively.
Since the gyroscopic affect imparted to each head 24' as it is rotated and swung from the stack of heads may not be sufficient to compensate for the affect of air resistance acting upon the elongated head when in the expanded position indicated in FIG. 8, a retarding device 128 is provided. The drag or retarding device is attached to the center of the upper wall 92 by a swivel mounted plurality of flexible lines 132 such as wires or cords.
The operation of the second embodiment of the invention is substantially the same as that of the first embodiment except that firing of each forward firing head 24' is controlled by the proximity fuze 102. The booster 103 of the fuze 102 fires when sufficiently radiated wave signal energy which energy was previously generated by the wave generator of the fuze and sent to the target, is collected from the target area and reflected back to the firing system by the reflector 110. The retarding device 128 serves to maintain the heads 24' aimed at the target. As indicated in FIG. 6, when the heads are fired, the fragmentation wall 94 breaks into its individual fragments 96 which first destroys the parts of the head 24' therebelow and then covers the target area with a conical pattern of fragments moving toward the target at very high speeds. It will also be noted that all fragments are directed toward the target as opposed to having some of the fragments being wasted by being directed outwardly to the sides or in a direction away from the target.
The forward firing system 20 of the third embodiment of the invention is illustrated in FIGS. 9-12. The system 20" differs from the first and second embodiments only in that the forward firing heads 24" differ somewhat from the previously described heads. Accordingly, only the heads 24 will be described in detail and parts which are similar to those described in the first embodiment of the invention will be assigned the same numerals followed by a double prime As indicated in FIGS. 11 and 12, each forward firing head 24 includes a shell having a cylindrical side wall 142 with a flange 144 on its lower end and with a concave upper wall 146 provided with a cavity for receiving a proximity fuze 148 which includes a detonator and a wave generator. A fragmentation wall 150 made up of a plurality of interconnected fragments 152 closes the lower end of the shell 140 and has an explosive charge 154 and a wave shaper 156 thereabove. It is to be understood that the wave shaper is optional. A combination reflector and retarding device 158 is shaped as a perforated dish 159 and is connected to the center of the proximity fuze 148 by swiveled and flexible connectors 160 as cables or the like.
As in the first embodiment of the invention, when the plurality of forward firing heads 24" are stacked in the bomb 22", they are interconnected by pins 62" which are secured to ears 162 in the forward firing heads 24 and project into radial edge slots 164 in the next adjacent head. The bomb 22" may be rotated about its longitudinal axis either by a rocket motor or by angled fins 32" on the tail assembly 30" as in the other two forms of the invention.
In operation of the third embodiment of the invention, after the stack of forward firing heads have been spun they are released from their missile 22" (FIG. 9). The heads then swing outwardly from the stack of heads and eventually assume the positions illustrated in FIG. 9 with the combined retarding devices and reflectors 158 in their extended positions. Each head 24 then moves toward the target until the signals from the wave generator that was previously reflected to the target area by the dished reflector 159 are reflected back to the fuze mechanism 148 by the targetand reflector 159. At the set altitude the proximity fuze 148 initiates the explosive train. The explosive charge 154 projects the fragmentation wall 150 onto the target area at high speed in conical patterns as indicated in FIG. 10.
From the foregoing description it. is apparent that the forward firing heads of the present invention are stacked in the missile and the missile is spun about its longitudinal axis either by angled "tail fins or a rocket motor to induce spin. The heads are released from the missile in response to the firing of a first time delay or proximity fuze in the nose cone of the missile. The rotated heads then independently disperse over a relatively wide area and gyroscopically retain their directional control with their fragmentation walls directed toward the target. The explosive charge in each head is then fired either in response to a time delay fuze or in response to an adjustable proximity fuze as in the other embodiments of the invention. A retarding device is provided on certain of the heads to retain orientation of the heads and to provide for more effective control of the firing of the heads. Since only one wall of each forward firing head is a fragmentation wall, and since that wall is directed toward the target, all frag ments are propelled against the target area upon explosion of the head and are not wasted by flying away from the target in other directions. I
Although the best mode contemplated for carrying out the present invention has been herein shown and described, it will be apparent that modification an d yariation may be made without departing from what is regarded to be the subject matter of the invention.
I claim, 1. A forward firing system comprising a missile movable in a forward direction toward a target area and including a tubular body; a plurality of explosive heads in the form of discs positioned in said body defining a stack of heads having a longitudinal axis; each head including an explosive charge, a fragmentation wall disposed only on the forward end of said explosive charge, and a thin walled housing enclosing the remaining portion of the head; means for rotating the stack of heads; means for simultaneously releasing all heads in said stack of heads from said body in response to the movement of the missile into range of the target area; connecting means for releasably interconnecting said heads in said stack and being responsive to rotation of said stack and to the release of said stack from said body for dispensing said heads from said stack and from each other in a plurality of different directions while retaining directional orientation of said heads relative to said target area; and means for thereafter detonating the explosive charge in each of said heads prior to the heads reaching the target area.
2. A forward firing system according to claim 1 wherein said detonating means is a proximity fuze.
3. A forward firing system according to claim 2 wherein each of said heads carries a signal wave generator and a signal reflector, and means mounting at least a portion of said reflector for movement from a compact stacked position against one end surface of said head to an extended reflecting position spaced from said one end of said head.
4. A forward firing system according to claim 3 wherein said one end is the forward end of said head, and additionally comprising forward expansible reflector supporting means movable between a compact position encompassed within said associated head when said head is in said stack, and an extended position forwardly of said forward end of the head after'the head has been swung away from said stack.
5. A forward firing system according to claim 3 wherein said one end is the rear end of said head and wherein said reflector is a concave dish which contacts 3 and conforms to the shape of the rear wall of said head when the head is in said stack, and which is spaced rearwardly of said rear wall in an operative reflecting position when the head is released from said stack, and extendible connecting means for connecting said reflector to said head when in its operative reflecting position.
6. A forward firing head according to claim 3 wherein said tubular body is a cylindrical housing having an axis of generation and wherein said signal reflector includes a plurality of resiliently stressed pie shaped leaves having their inner ends connected to the forward end of said housing about said axis of generation and having their outer ends free to move forwardly away from said forward end, and means engaging the free ends of said pie shaped leaves for bowing said leaves by moving the outer ends of said leaves forwardly away from said fragmentation wall in position to define a parabolic reflector for sending and collecting signals reflected back from the target area.
7. A forward firing head according to claim 6 and additionally comprising forwardly extendible resilient means movable between a compact position encompassed by said housing and an extended position projecting forwardly of said housing, said antenna being mounted on the projectable end of said extendible resilient means.
8. A forward firing head according to claim 1 wherein said fragmentation wall is a planar wall.
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US2317256 *||Nov 20, 1940||Apr 20, 1943||De Kurowski Juljan Bronislaw||Bomb dropping device adapted to be dropped from aircraft|
|US2432920 *||Apr 29, 1942||Dec 16, 1947||Mckay Herbert Couchman||Radiation-controlled release for aerial bombs or other loads|
|US2972949 *||Jan 18, 1956||Feb 28, 1961||Macleod Norman A||Anti-personnel fragmentation weapon|
|US3093072 *||Jan 30, 1957||Jun 11, 1963||Pigman George L||Spin-induced dispersal bomb|
|US3388664 *||Sep 28, 1965||Jun 18, 1968||Sanders Associates Inc||Extensible fuse extender|
|US3500714 *||Dec 14, 1967||Mar 17, 1970||Fmc Corp||Apparatus for launching projectiles|
|US3646888 *||Mar 27, 1969||Mar 7, 1972||Explosive Tech||Aerodynamic directional grenade, launcher therefor and weapons system utilizing the same|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US4264045 *||Sep 4, 1979||Apr 28, 1981||Avco Corporation||Despinning method and apparatus|
|US4356770 *||Nov 9, 1979||Nov 2, 1982||Avco Corporation||Overflying munitions device and system|
|US4505203 *||Feb 4, 1983||Mar 19, 1985||Honeywell Inc.||Frangible ballast|
|US4555971 *||Jul 14, 1982||Dec 3, 1985||Rheinmetall Gmbh||Method and apparatus for covering a target area with ammunition|
|US4584943 *||Jul 9, 1984||Apr 29, 1986||Rheinmetall Gmbh||Missile head to be released in an airplane cargo drop or from a flying body|
|US4587902 *||Jul 25, 1984||May 13, 1986||Diehl Gmbh & Co.||Subordinate-ammunition member with target-detecting arrangement|
|US4616567 *||Jun 20, 1985||Oct 14, 1986||Rheinmetall Gmbh||Method and apparatus for covering a target area with ammunition|
|US4622900 *||Jun 25, 1984||Nov 18, 1986||Rheinmetall Gmbh||Exploding missile|
|US4691636 *||Jul 17, 1986||Sep 8, 1987||Rheinmetall Gmbh||Exploding missile|
|US4754706 *||Jan 15, 1987||Jul 5, 1988||Etienne Lacroix Tous Artifices||Munition scattering projectile|
|US4825766 *||Mar 6, 1979||May 2, 1989||Emi Limited||Fuzing arrangements|
|US4848235 *||Aug 2, 1988||Jul 18, 1989||Diehl Gmbh & Co.||Submunition member with laterally outwardly-movable target detection device|
|US5138947 *||May 23, 1991||Aug 18, 1992||Rheinmetall Gmbh||Flying body including a target detection device|
|US5723811 *||Jun 16, 1997||Mar 3, 1998||Tda Armements Sas||Warhead having a core generating charge|
|US6834593 *||Aug 19, 2003||Dec 28, 2004||Textron Systems Corporation||Self extracting submunition|
|US6920827||Oct 31, 2003||Jul 26, 2005||Raytheon Company||Vehicle-borne system and method for countering an incoming threat|
|US6931994||Nov 21, 2002||Aug 23, 2005||Raytheon Company||Tandem warhead|
|US6945088 *||May 14, 2002||Sep 20, 2005||The United States Of America As Represented By The Secretary Of The Navy||Multi-fragment impact test specimen|
|US6973878||Jun 5, 2003||Dec 13, 2005||Raytheon Company||Warhead with aligned projectiles|
|US7017496||Mar 10, 2003||Mar 28, 2006||Raytheon Company||Kinetic energy rod warhead with imploding charge for isotropic firing of the penetrators|
|US7066093 *||Jun 6, 2001||Jun 27, 2006||Bae Systems Bofors Ab||Modular warhead for units of ammunition such as missiles|
|US7127995 *||Jun 20, 2001||Oct 31, 2006||Bae Systems Bofors Ab||Device for adapting a unit of ammunition for different types of targets and situations|
|US7143698||May 13, 2005||Dec 5, 2006||Raytheon Company||Tandem warhead|
|US7412916||Jan 18, 2006||Aug 19, 2008||Raytheon Company||Fixed deployed net for hit-to-kill vehicle|
|US7415917||Mar 10, 2003||Aug 26, 2008||Raytheon Company||Fixed deployed net for hit-to-kill vehicle|
|US7448324 *||Aug 9, 2006||Nov 11, 2008||At&T Intellectual Property Ii, L.P.||Segmented rod projectile|
|US7621222||Feb 17, 2005||Nov 24, 2009||Raytheon Company||Kinetic energy rod warhead with lower deployment angles|
|US7624682||Feb 17, 2005||Dec 1, 2009||Raytheon Company||Kinetic energy rod warhead with lower deployment angles|
|US7624683||Jul 20, 2005||Dec 1, 2009||Raytheon Company||Kinetic energy rod warhead with projectile spacing|
|US7717042||Jan 6, 2005||May 18, 2010||Raytheon Company||Wide area dispersal warhead|
|US7726244||Jul 20, 2007||Jun 1, 2010||Raytheon Company||Mine counter measure system|
|US7930978||Nov 17, 2008||Apr 26, 2011||Raytheon Company||Forward firing fragmentation warhead|
|US7971535||May 19, 2008||Jul 5, 2011||Raytheon Company||High-lethality low collateral damage fragmentation warhead|
|US8006623||Nov 17, 2008||Aug 30, 2011||Raytheon Company||Dual-mass forward and side firing fragmentation warhead|
|US8127686||Jul 20, 2005||Mar 6, 2012||Raytheon Company||Kinetic energy rod warhead with aiming mechanism|
|US8272326 *||Nov 11, 2011||Sep 25, 2012||Raytheon Company||Methods and apparatus for high-impulse fuze booster for insensitive munitions|
|US8418623||Apr 2, 2010||Apr 16, 2013||Raytheon Company||Multi-point time spacing kinetic energy rod warhead and system|
|US8528480 *||May 15, 2008||Sep 10, 2013||Rheinmetall Waffe Munition Gmbh||Warhead|
|US20030172833 *||Jun 20, 2001||Sep 18, 2003||Torsten Ronn||Device for adapting a unit of ammunition for different types of targets and situations|
|US20040011238 *||Jun 6, 2001||Jan 22, 2004||Torsten Ronn||Modular warhead for units of ammunition such as missiles|
|US20040055498 *||Feb 20, 2003||Mar 25, 2004||Lloyd Richard M.||Kinetic energy rod warhead deployment system|
|US20040107861 *||Aug 19, 2003||Jun 10, 2004||Textron Systems Corporation||Self extracting submunition|
|US20040200380 *||Jun 6, 2003||Oct 14, 2004||Lloyd Richard M.||Kinetic energy rod warhead with lower deployment angles|
|US20050109234 *||Sep 10, 2004||May 26, 2005||Lloyd Richard M.||Kinetic energy rod warhead with lower deployment angles|
|US20050115450 *||Oct 31, 2003||Jun 2, 2005||Lloyd Richard M.||Vehicle-borne system and method for countering an incoming threat|
|US20050126421 *||Nov 21, 2002||Jun 16, 2005||Lloyd Richard M.||Tandem warhead|
|US20050132923 *||Mar 10, 2003||Jun 23, 2005||Lloyd Richard M.||Fixed deployed net for hit-to-kill vehicle|
|US20060021538 *||Oct 7, 2004||Feb 2, 2006||Lloyd Richard M||Kinetic energy rod warhead deployment system|
|US20060086279 *||Feb 17, 2005||Apr 27, 2006||Lloyd Richard M||Kinetic energy rod warhead with lower deployment angles|
|US20060112817 *||Jan 18, 2006||Jun 1, 2006||Lloyd Richard M||Fixed deployed net for hit-to-kill vehicle|
|US20060112847 *||Jan 6, 2005||Jun 1, 2006||Lloyd Richard M||Wide area dispersal warhead|
|US20060162604 *||May 13, 2005||Jul 27, 2006||Lloyd Richard M||Tandem warhead|
|US20060283348 *||Jul 20, 2005||Dec 21, 2006||Lloyd Richard M||Kinetic energy rod warhead with self-aligning penetrators|
|US20120055366 *||Nov 11, 2011||Mar 8, 2012||Raytheon Company||Methods and apparatus for high-impulse fuze booster for insensitive munitions|
|US20140083402 *||Sep 23, 2012||Mar 27, 2014||L.H.B. Ltd.||Clay-pigeon-like projectile for crowd control|
|USRE32094 *||Oct 31, 1984||Mar 25, 1986||Avco Corporation||Overflying munitions device and system|
|DE2757141A1 *||Dec 21, 1977||Jul 6, 1978||Bofors Ab||Einrichtung zum bremsen eines rotierenden koerpers|
|DE3042063A1 *||Nov 7, 1980||Dec 2, 1982||Avco Corp||Munitionssystem (werfergeschoss) und vorrichtung zum abfeuern desselben|
|DE3237483A1 *||Oct 9, 1982||May 3, 1984||Licentia Gmbh||Arrangement for the contactless electrical ignition of explosive charges|
|DE19749168A1 *||Nov 7, 1997||May 12, 1999||Diehl Stiftung & Co||Large caliber missile warhead has eccentrically arranged sub-munitions in several payload stages|
|WO2008145259A1||May 15, 2008||Dec 4, 2008||Rheinmetall Waffe Munition||Warhead|
|WO2009046166A1 *||Oct 2, 2008||Apr 9, 2009||Donald Wayne Allen||Systems and methods for reducing drag and/or vortex induced vibration|
|WO2009142789A2 *||Feb 26, 2009||Nov 26, 2009||Raytheon Company||High-lethality low collateral damage forward firing fragmentation warhead|
|WO2009142789A3 *||Feb 26, 2009||Jan 14, 2010||Raytheon Company||High-lethality low collateral damage forward firing fragmentation warhead|
|WO2015049411A1 *||Oct 2, 2013||Apr 9, 2015||Leijona Instituutti Oy||Munition|
|U.S. Classification||102/389, 102/214, 102/213, 102/393|
|International Classification||F42B12/02, F42B12/20, F42B10/56, F42B12/58, F42B10/00|
|Cooperative Classification||F42B12/204, F42B10/56, F42B12/208, F42B12/58, F42B12/202|
|European Classification||F42B12/20B2, F42B12/20B4, F42B12/20F, F42B10/56, F42B12/58|