US3818833A - Independent multiple head forward firing system - Google Patents

Independent multiple head forward firing system Download PDF

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Publication number
US3818833A
US3818833A US00281904A US28190472A US3818833A US 3818833 A US3818833 A US 3818833A US 00281904 A US00281904 A US 00281904A US 28190472 A US28190472 A US 28190472A US 3818833 A US3818833 A US 3818833A
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Prior art keywords
heads
head
stack
missile
reflector
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Expired - Lifetime
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US00281904A
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English (en)
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G Throner
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FMC Corp
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FMC Corp
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Priority to US00281904A priority Critical patent/US3818833A/en
Priority to DE19732340653 priority patent/DE2340653A1/de
Priority to BE134598A priority patent/BE803629A/fr
Priority to IT52020/73A priority patent/IT990254B/it
Priority to FR7330028A priority patent/FR2217660A1/fr
Application granted granted Critical
Publication of US3818833A publication Critical patent/US3818833A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • F42B12/201—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type characterised by target class
    • F42B12/202—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type characterised by target class for attacking land area or area targets, e.g. airburst
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/56—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding of parachute or paraglider type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • F42B12/201—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type characterised by target class
    • F42B12/204—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type characterised by target class for attacking structures, e.g. specific buildings or fortifications, ships or vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • F42B12/208—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type characterised by a plurality of charges within a single high explosive warhead
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles

Definitions

  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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 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.
  • 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.
  • the heads 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.
  • 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.
  • 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.
  • a forward firing system according to claim 1 wherein said detonating means is a proximity fuze.
  • 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.
  • a forward firing system 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.
  • a forward firing system 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.
  • a forward firing head 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.
  • 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.
  • a forward firing head according to claim 1 wherein said fragmentation wall is a planar wall.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US00281904A 1972-08-18 1972-08-18 Independent multiple head forward firing system Expired - Lifetime US3818833A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US00281904A US3818833A (en) 1972-08-18 1972-08-18 Independent multiple head forward firing system
DE19732340653 DE2340653A1 (de) 1972-08-18 1973-08-10 Geschosswaffe
BE134598A BE803629A (fr) 1972-08-18 1973-08-14 Dispositif de mise a feu anticipee
IT52020/73A IT990254B (it) 1972-08-18 1973-08-14 Sistema a proiezione conica verso l avanti in missili a testa con ele menti multipli indipendenti
FR7330028A FR2217660A1 (fr) 1972-08-18 1973-08-17

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US00281904A US3818833A (en) 1972-08-18 1972-08-18 Independent multiple head forward firing system

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US3818833A true US3818833A (en) 1974-06-25

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US00281904A Expired - Lifetime US3818833A (en) 1972-08-18 1972-08-18 Independent multiple head forward firing system

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US (1) US3818833A (fr)
BE (1) BE803629A (fr)
DE (1) DE2340653A1 (fr)
FR (1) FR2217660A1 (fr)
IT (1) IT990254B (fr)

Cited By (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2757141A1 (de) * 1976-12-27 1978-07-06 Bofors Ab Einrichtung zum bremsen eines rotierenden koerpers
US4264045A (en) * 1979-09-04 1981-04-28 Avco Corporation Despinning method and apparatus
US4356770A (en) * 1979-11-09 1982-11-02 Avco Corporation Overflying munitions device and system
DE3237483A1 (de) * 1982-10-09 1984-05-03 Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt Anordnung zum kontaktlosen elektrischen anzuenden von explosiven ladungen
US4505203A (en) * 1983-02-04 1985-03-19 Honeywell Inc. Frangible ballast
US4555971A (en) * 1981-07-14 1985-12-03 Rheinmetall Gmbh Method and apparatus for covering a target area with ammunition
USRE32094E (en) * 1979-11-09 1986-03-25 Avco Corporation Overflying munitions device and system
US4584943A (en) * 1983-07-07 1986-04-29 Rheinmetall Gmbh Missile head to be released in an airplane cargo drop or from a flying body
US4587902A (en) * 1983-07-26 1986-05-13 Diehl Gmbh & Co. Subordinate-ammunition member with target-detecting arrangement
US4622900A (en) * 1983-06-25 1986-11-18 Rheinmetall Gmbh Exploding missile
US4754706A (en) * 1983-06-27 1988-07-05 Etienne Lacroix Tous Artifices Munition scattering projectile
USH540H (en) 1987-08-20 1988-11-01 The United States Of America As Represented By The Secretary Of The Army Explosive shock attenuator for high fragment velocity warheads
US4825766A (en) * 1978-03-11 1989-05-02 Emi Limited Fuzing arrangements
US4848235A (en) * 1986-09-12 1989-07-18 Diehl Gmbh & Co. Submunition member with laterally outwardly-movable target detection device
US5138947A (en) * 1990-05-30 1992-08-18 Rheinmetall Gmbh Flying body including a target detection device
US5723811A (en) * 1995-06-13 1998-03-03 Tda Armements Sas Warhead having a core generating charge
DE19749168A1 (de) * 1997-11-07 1999-05-12 Diehl Stiftung & Co Gefechtskopf für eine Rakete
SG93206A1 (en) * 1998-05-29 2002-12-17 Israel Military Ind Projectile
US20030172833A1 (en) * 2000-07-03 2003-09-18 Torsten Ronn Device for adapting a unit of ammunition for different types of targets and situations
US20040011238A1 (en) * 2000-07-03 2004-01-22 Torsten Ronn Modular warhead for units of ammunition such as missiles
US20040055498A1 (en) * 2002-08-29 2004-03-25 Lloyd Richard M. Kinetic energy rod warhead deployment system
US20040107861A1 (en) * 2001-11-16 2004-06-10 Textron Systems Corporation Self extracting submunition
US20040200380A1 (en) * 2001-08-23 2004-10-14 Lloyd Richard M. Kinetic energy rod warhead with lower deployment angles
US20050109234A1 (en) * 2001-08-23 2005-05-26 Lloyd Richard M. Kinetic energy rod warhead with lower deployment angles
US20050115450A1 (en) * 2003-10-31 2005-06-02 Lloyd Richard M. Vehicle-borne system and method for countering an incoming threat
US20050126421A1 (en) * 2002-08-29 2005-06-16 Lloyd Richard M. Tandem warhead
US20050132923A1 (en) * 2002-08-29 2005-06-23 Lloyd Richard M. Fixed deployed net for hit-to-kill vehicle
US6945088B2 (en) * 2002-05-14 2005-09-20 The United States Of America As Represented By The Secretary Of The Navy Multi-fragment impact test specimen
US6973878B2 (en) 2001-06-04 2005-12-13 Raytheon Company Warhead with aligned projectiles
US20060021538A1 (en) * 2002-08-29 2006-02-02 Lloyd Richard M Kinetic energy rod warhead deployment system
US7017496B2 (en) 2002-08-29 2006-03-28 Raytheon Company Kinetic energy rod warhead with imploding charge for isotropic firing of the penetrators
US20060086279A1 (en) * 2001-08-23 2006-04-27 Lloyd Richard M Kinetic energy rod warhead with lower deployment angles
US20060112847A1 (en) * 2004-11-29 2006-06-01 Lloyd Richard M Wide area dispersal warhead
US20060283348A1 (en) * 2001-08-23 2006-12-21 Lloyd Richard M Kinetic energy rod warhead with self-aligning penetrators
US7448324B1 (en) * 2006-05-03 2008-11-11 At&T Intellectual Property Ii, L.P. Segmented rod projectile
WO2008145259A1 (fr) 2007-05-30 2008-12-04 Rheinmetall Waffe Munition Gmbh Ogive
WO2009046166A1 (fr) * 2007-10-05 2009-04-09 Shell Oil Company Systèmes et procédés de réduction des vibrations induites par tourbillon et/ou traînée
US20090205529A1 (en) * 2001-08-23 2009-08-20 Lloyd Richard M Kinetic energy rod warhead with lower deployment angles
US7624683B2 (en) 2001-08-23 2009-12-01 Raytheon Company Kinetic energy rod warhead with projectile spacing
WO2009142789A3 (fr) * 2008-05-19 2010-01-14 Raytheon Company Ogive à fragmentation de tir avant, à faibles dommages collatéraux et à mortalité élevée
US7726244B1 (en) 2003-10-14 2010-06-01 Raytheon Company Mine counter measure system
US20110146523A1 (en) * 2008-05-19 2011-06-23 Raytheon Company High-lethality low collateral damage fragmentation warhead
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US20120055366A1 (en) * 2008-04-25 2012-03-08 Raytheon Company Methods and apparatus for high-impulse fuze booster for insensitive munitions
KR101200802B1 (ko) 2010-04-14 2012-11-13 국방과학연구소 파편링을 구비한 공중폭발탄
US8418623B2 (en) 2010-04-02 2013-04-16 Raytheon Company Multi-point time spacing kinetic energy rod warhead and system
US20140083402A1 (en) * 2012-09-23 2014-03-27 L.H.B. Ltd. Clay-pigeon-like projectile for crowd control
US20140144311A1 (en) * 2011-07-14 2014-05-29 Nahum Orlev Wide area neutralizer
WO2015049411A1 (fr) * 2013-10-02 2015-04-09 Leijona Instituutti Oy Munition
US9528802B1 (en) * 2015-11-19 2016-12-27 The United States Of America As Represented By The Secretary Of The Army Indirect fire munition non-lethal cargo carrier mortar

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2523717B1 (fr) * 1982-03-17 1987-04-30 Stauff Emile Systeme d'arme, notamment antichar
DE3427227A1 (de) * 1984-07-24 1986-01-30 Diehl GmbH & Co, 8500 Nürnberg Endphasen-steuerbarer munitionsartikel und verfahren zu seiner zielnavigation
DE3437307C1 (de) * 1984-10-11 1985-12-12 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Munition
EP0735342B1 (fr) * 1994-09-15 2000-01-12 Konstruktorskoe Bjuro Mashinostroenia Munition pour l'autodefense d'un char de combat
DE29507361U1 (de) * 1995-05-08 1996-09-26 Diehl GmbH & Co, 90478 Nürnberg Submunition
RU2363923C1 (ru) * 2008-04-04 2009-08-10 Государственное Образовательное Учреждение Высшего Профессионального Образования "Московский Государственный Технический Университет Имени Н.Э. Баумана" Танковый кассетный снаряд "лихославль" с осколочными субснарядами
RU2400698C1 (ru) * 2009-04-09 2010-09-27 Государственное Образовательное Учреждение Высшего Профессионального Образования "Московский Государственный Технический Университет Имени Н.Э. Баумана" Танковый кассетный снаряд "выбрынь" с осколочными боевыми элементами

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2317256A (en) * 1939-11-21 1943-04-20 Kurowski Juljan Bronislaw De Bomb dropping device adapted to be dropped from aircraft
US2432920A (en) * 1942-04-29 1947-12-16 Mckay Herbert Couchman Radiation-controlled release for aerial bombs or other loads
US2972949A (en) * 1956-01-18 1961-02-28 Norman A Macleod Anti-personnel fragmentation weapon
US3093072A (en) * 1957-01-30 1963-06-11 George L Pigman Spin-induced dispersal bomb
US3388664A (en) * 1965-09-28 1968-06-18 Sanders Associates Inc Extensible fuse extender
US3500714A (en) * 1967-12-14 1970-03-17 Fmc Corp Apparatus for launching projectiles
US3646888A (en) * 1969-03-27 1972-03-07 Explosive Tech Aerodynamic directional grenade, launcher therefor and weapons system utilizing the same

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2317256A (en) * 1939-11-21 1943-04-20 Kurowski Juljan Bronislaw De Bomb dropping device adapted to be dropped from aircraft
US2432920A (en) * 1942-04-29 1947-12-16 Mckay Herbert Couchman Radiation-controlled release for aerial bombs or other loads
US2972949A (en) * 1956-01-18 1961-02-28 Norman A Macleod Anti-personnel fragmentation weapon
US3093072A (en) * 1957-01-30 1963-06-11 George L Pigman Spin-induced dispersal bomb
US3388664A (en) * 1965-09-28 1968-06-18 Sanders Associates Inc Extensible fuse extender
US3500714A (en) * 1967-12-14 1970-03-17 Fmc Corp Apparatus for launching projectiles
US3646888A (en) * 1969-03-27 1972-03-07 Explosive Tech Aerodynamic directional grenade, launcher therefor and weapons system utilizing the same

Cited By (84)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2757141A1 (de) * 1976-12-27 1978-07-06 Bofors Ab Einrichtung zum bremsen eines rotierenden koerpers
US4825766A (en) * 1978-03-11 1989-05-02 Emi Limited Fuzing arrangements
US4264045A (en) * 1979-09-04 1981-04-28 Avco Corporation Despinning method and apparatus
US4356770A (en) * 1979-11-09 1982-11-02 Avco Corporation Overflying munitions device and system
DE3042063A1 (de) * 1979-11-09 1982-12-02 Avco Corp., 06830 Greenwich, Conn. Munitionssystem (werfergeschoss) und vorrichtung zum abfeuern desselben
USRE32094E (en) * 1979-11-09 1986-03-25 Avco Corporation Overflying munitions device and system
US4616567A (en) * 1981-07-14 1986-10-14 Rheinmetall Gmbh Method and apparatus for covering a target area with ammunition
US4555971A (en) * 1981-07-14 1985-12-03 Rheinmetall Gmbh Method and apparatus for covering a target area with ammunition
DE3237483A1 (de) * 1982-10-09 1984-05-03 Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt Anordnung zum kontaktlosen elektrischen anzuenden von explosiven ladungen
US4505203A (en) * 1983-02-04 1985-03-19 Honeywell Inc. Frangible ballast
US4691636A (en) * 1983-06-25 1987-09-08 Rheinmetall Gmbh Exploding missile
US4622900A (en) * 1983-06-25 1986-11-18 Rheinmetall Gmbh Exploding missile
US4754706A (en) * 1983-06-27 1988-07-05 Etienne Lacroix Tous Artifices Munition scattering projectile
US4584943A (en) * 1983-07-07 1986-04-29 Rheinmetall Gmbh Missile head to be released in an airplane cargo drop or from a flying body
US4587902A (en) * 1983-07-26 1986-05-13 Diehl Gmbh & Co. Subordinate-ammunition member with target-detecting arrangement
US4848235A (en) * 1986-09-12 1989-07-18 Diehl Gmbh & Co. Submunition member with laterally outwardly-movable target detection device
USH540H (en) 1987-08-20 1988-11-01 The United States Of America As Represented By The Secretary Of The Army Explosive shock attenuator for high fragment velocity warheads
US5138947A (en) * 1990-05-30 1992-08-18 Rheinmetall Gmbh Flying body including a target detection device
US5723811A (en) * 1995-06-13 1998-03-03 Tda Armements Sas Warhead having a core generating charge
DE19749168A1 (de) * 1997-11-07 1999-05-12 Diehl Stiftung & Co Gefechtskopf für eine Rakete
SG93206A1 (en) * 1998-05-29 2002-12-17 Israel Military Ind Projectile
US20030172833A1 (en) * 2000-07-03 2003-09-18 Torsten Ronn Device for adapting a unit of ammunition for different types of targets and situations
US20040011238A1 (en) * 2000-07-03 2004-01-22 Torsten Ronn Modular warhead for units of ammunition such as missiles
US7066093B2 (en) * 2000-07-03 2006-06-27 Bae Systems Bofors Ab Modular warhead for units of ammunition such as missiles
US7127995B2 (en) * 2000-07-03 2006-10-31 Bae Systems Bofors Ab Device for adapting a unit of ammunition for different types of targets and situations
US6973878B2 (en) 2001-06-04 2005-12-13 Raytheon Company Warhead with aligned projectiles
US20050109234A1 (en) * 2001-08-23 2005-05-26 Lloyd Richard M. Kinetic energy rod warhead with lower deployment angles
US7624682B2 (en) 2001-08-23 2009-12-01 Raytheon Company Kinetic energy rod warhead with lower deployment angles
US7624683B2 (en) 2001-08-23 2009-12-01 Raytheon Company Kinetic energy rod warhead with projectile spacing
US7621222B2 (en) 2001-08-23 2009-11-24 Raytheon Company Kinetic energy rod warhead with lower deployment angles
US20090205529A1 (en) * 2001-08-23 2009-08-20 Lloyd Richard M Kinetic energy rod warhead with lower deployment angles
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US20040200380A1 (en) * 2001-08-23 2004-10-14 Lloyd Richard M. Kinetic energy rod warhead with lower deployment angles
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US20060086279A1 (en) * 2001-08-23 2006-04-27 Lloyd Richard M Kinetic energy rod warhead with lower deployment angles
US6834593B2 (en) * 2001-11-16 2004-12-28 Textron Systems Corporation Self extracting submunition
US20040107861A1 (en) * 2001-11-16 2004-06-10 Textron Systems Corporation Self extracting submunition
US6945088B2 (en) * 2002-05-14 2005-09-20 The United States Of America As Represented By The Secretary Of The Navy Multi-fragment impact test specimen
US20060162604A1 (en) * 2002-08-29 2006-07-27 Lloyd Richard M Tandem warhead
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US20050126421A1 (en) * 2002-08-29 2005-06-16 Lloyd Richard M. Tandem warhead
US20050132923A1 (en) * 2002-08-29 2005-06-23 Lloyd Richard M. Fixed deployed net for hit-to-kill vehicle
US20040055498A1 (en) * 2002-08-29 2004-03-25 Lloyd Richard M. Kinetic energy rod warhead deployment system
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US6920827B2 (en) 2003-10-31 2005-07-26 Raytheon Company Vehicle-borne system and method for countering an incoming threat
US20050115450A1 (en) * 2003-10-31 2005-06-02 Lloyd Richard M. Vehicle-borne system and method for countering an incoming threat
US7717042B2 (en) 2004-11-29 2010-05-18 Raytheon Company Wide area dispersal warhead
US20060112847A1 (en) * 2004-11-29 2006-06-01 Lloyd Richard M Wide area dispersal warhead
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US8528480B2 (en) * 2007-05-30 2013-09-10 Rheinmetall Waffe Munition Gmbh Warhead
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US20100192797A1 (en) * 2007-05-30 2010-08-05 Rheinmetall Waffe Munition Gmbh Warhead
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DE2340653A1 (de) 1974-04-04
FR2217660A1 (fr) 1974-09-06
IT990254B (it) 1975-06-20
BE803629A (fr) 1973-12-03

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