EP0051375A2 - Projectile pour la destruction de matériel militaire - Google Patents

Projectile pour la destruction de matériel militaire Download PDF

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Publication number
EP0051375A2
EP0051375A2 EP81304816A EP81304816A EP0051375A2 EP 0051375 A2 EP0051375 A2 EP 0051375A2 EP 81304816 A EP81304816 A EP 81304816A EP 81304816 A EP81304816 A EP 81304816A EP 0051375 A2 EP0051375 A2 EP 0051375A2
Authority
EP
European Patent Office
Prior art keywords
projectile
projectile according
impact
alloy
frangible
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP81304816A
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German (de)
English (en)
Other versions
EP0051375B1 (fr
EP0051375A3 (en
Inventor
Fritz K Feldmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pacific Technica Corp
Original Assignee
Pacific Technica Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Pacific Technica Corp filed Critical Pacific Technica Corp
Priority to AT81304816T priority Critical patent/ATE40004T1/de
Publication of EP0051375A2 publication Critical patent/EP0051375A2/fr
Publication of EP0051375A3 publication Critical patent/EP0051375A3/en
Application granted granted Critical
Publication of EP0051375B1 publication Critical patent/EP0051375B1/fr
Expired legal-status Critical Current

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Classifications

    • 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
    • F42B12/367—Projectiles fragmenting upon impact without the use of explosives, the fragments creating a wounding or lethal effect
    • 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
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/06—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with hard or heavy core; Kinetic energy penetrators
    • 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
    • F42B12/22—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 with fragmentation-hull construction
    • 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
    • F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
    • F42B12/74—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the core or solid body

Definitions

  • the present invention relates to an anti-materiel projectile.
  • Ground-based air defence gun systems of 20mm and larger calibers presently in service employ conventional high explosive projectiles for defeating a target.
  • high explosive projectiles have good terminal effectiveness against aircraft, their inherent exterior ballistic performance is such as to result in poor hit probability in employment against high speed aircraft.
  • High explosive projectiles contain a fuse mechanism and a high explosive filler. These components are rather voluminous and of low weight, thus adversely restricting the sectional density of the projectile.
  • the resultant ballistic coefficient is such as to induce a high degree of velocity decay as a function of range and correspondingly long time of flight.
  • the long time of flight requires very large lead angles and superelevation angles. In the case of advanced ground-support aircraft, these angles are of such magnitudes that even with the use of sophisticated fire control systems the resultant hit probabilities are inadequate.
  • High velocity projectiles with short times of flight are essential for achievement of high hit probabilities regardless of the degree of sophistication of fire control system.
  • the desired short times of flight can be attained through the use of sabot-launched subcaliber projectiles having a high muzzle velocity as described in my U.S. Patent No. 3,714,900, "Discarding Sabot Projectiles".
  • the subcaliber projectiles should have a high sectional density, i.e. should consist of a high density material, such as a tungsten alloy for example, having a density of approximately 16 to 19 g/cm 3 .
  • Armor-piercing projectiles are of limited terminal effectiveness against soft targets such as high speed aircraft in that the projectile can hit the target causing superficial damage without destroying it.
  • the object of the invention is to provide a projectile design characteristic enabling a projectile to be designed with aballistic performance resulting in short times of flight and related high hit probabilities and simultaneously enabling a design providing the terminal ballistic effectiveness required to defeat aircraft and helicopter-type targets.
  • an explosive-free anti-materiel projectile characterised in that it relies for its destructive capability upon whole or partial structural fragmentation induced by impact shock at the target, followed by forward expansion of the clustered fragments under residual kinetic energy and combustion of structural components.
  • this invention is directed to ammunition for ground-based air defence systems in which a high density, frangible alloy used with a discarding-sabot projectile provides the desired terminal ballistics for the destruction of aircraft and similar battlefield targets.
  • the subcaliber projectile maintains the exterior ballistic efficiency and related high hit probability characteristics of subcaliber projectiles.
  • the novel concept eliminates the need for a fuse and high explosive commonly used in air-defence ammunition. Because of its effectiveness against a considerable variety of battlefield targets, including armor, the novel projectile has been named "anti-materiel projectile".
  • the subcaliber projectile of the discarding-sabot ammunition is preferably spin-stabilised and consists either entirely or predominantly of a frangible, high, density material. Its operation does not require the provision of either high explosive or a fuse. Upon impact on a target such as an aircraft, the fragmentation of the frangible material is induced by the impact shock wave and the subsequent expansion passing through the projectile body. The resultant fragmentation is nearly uniform throughout the frangible mass. Prenotching or prefragmentation during manufacture is neither required nor desired.
  • the high density fragments are projected into the target in an expanding cluster under the influence of the residual flight velocity and the centrifugal velocity induced by the residual projectile spin. Damage to the aircraft and its components is imparted through impact and/or penetration by high velocity fragments.
  • the damage to the aircraft due to the high speed fragments can be enhanced through the incorporation of pyrophoric metal components in the projectile such as zirconium, titanium, or depleted uranium alloy, which is also fractured and which then ignites due to the impact shock loads.
  • pyrophoric metal components in the projectile such as zirconium, titanium, or depleted uranium alloy, which is also fractured and which then ignites due to the impact shock loads.
  • the resultant exothermic reaction yielding fragments burning at the temperatures up to approximately 3000°C, induces pyrophoric effects capable of igniting a variety of combustibles such as gasoline and jet fuel, thereby contributing to the terminal effectiveness of the projectile.
  • the frangible projectile can be equipped with a pyrophoric tracer.
  • the projectile may be provided with a self-destruct mechanism to avoid hazards to friendly personnel, equipment, or installations from projectiles not hitting the target. In this case destruction is timed by the burning of a tracer and is induced by a propellant charge fracturing the frangible projectile body.
  • a projectile body consisting in part of a frangible material and in part of a high strength alloy.
  • Such composite projectiles permit the defeat of spaced multiple plate targets as represented, for example, by aircraft or helicopters equipped with armored cockpits or other protected components.
  • the preferred projectile of the invention has the following characteristics:-
  • the discarding-sabot subcaliber projectile assembly contains the subcaliber projectile 12 in a coaxial position and consists essentially of three components as described in U.S. Patent 3,714,900.
  • the sabot nose 14 envelopes the subcaliber projectile.
  • the rear of the sabot consists of the sabot base 16 provided with a rotating band 18 preferably manufactured of injection molded plastic as described in my U.S. Patent 3,786,760.
  • the discarding-sabot subcaliber projectile assembly is generally attached to a conventional primed cartridge case 20 containing a propellant 22. Upon firing and emergence from the muzzle of the gun, the sabot components are automatically discarded in a manner described in U.S. Patent No. 3,714,900 and the subcaliber projectile proceeds along the line of fire at high .velocity.
  • the projectile 12 shown in Figures 2 and 3 comprises a main body portion ⁇ 24 with cylindrical central section 25, tapered nose 26, and tapered base 27 sections.
  • the main projectile body 24 consists of a frangible, high density alloy.
  • the projectile tip (or windscreen) 28 is preferably manufactured of a pyrophoric metal such as zirconium alloy, titanium, or depleted uranium alloy.
  • the two components can be assembled by a variety of known methods. In the - configuration shown in Figure 2, assembly is accomplished by means of a press fit at the interface of the nipple-shaped extension 29 of the pyrophoric metal projectile tip and the main projectile body. If desirable, the extension 29 may extend rearward through the entire length of the main projectile body as shown in Figure 3.
  • the pyrophoric metal projectile tip is optional and may be omitted as in the case of very small caliber projectiles. In that case the entire subcaliber projectile consists of the high density frangible material as shown in Figure 1 incorporating the single element subcaliber projectile.
  • the frangible high density metal of the subcaliber projectile which is part of this invention provides specific strength properties to enable the desired operation.
  • the metal has the compressive strength to withstand the longitudinal acceleration experienced by the projectile upon firing from the gun. These accelerations may exceed 175,000 g's for a short duration requiring a compressive strength in excess of 15,000 kg/cm 2 .
  • the subcaliber projectile experiences an impact shock wave propagated rearward through the projectile.
  • the material experiences expansion. This expansion results in high tensile loads which lead to the fracturing of the material, a process referred to as spalling.
  • the tensile strength of the projectile material has to be sufficiently low, e.g. approximately 800 kg/cm 2 , or within + 10%.
  • the frangible material of the subcaliber projectile has specific physical and mechanical properties to enable successful operation.
  • its density should be high, preferably in the range of 17 to 19 g/cm 3 , to arrive at a high ballistic coefficient for efficient exterior ballistics performance characterised by short time of flight, flat trajectory and minimal velocity decay.
  • the material has to provide a high dynamic compressive strength to withstand the launch acceleration experienced in the gun.
  • the tensile strength of.the material should be low to assure proper projectile fragmentation at reduced impact velocities against thin skinned aircraft structures.
  • the magnitude of the dynamic strength properties depend on the caliber and other specific parameters of the projectile-gun system. As an example, the characteristics for a typical 35 mm discarding-sabot air-defence projectile are listed below:
  • the desired unique properties can be attained using solid state, fusion sintered, commercial grade tungsten. Subsequent to sintering, the material is annealed prior to machining. In this state, the material has a high degree of brittleness and when exposed to an impact shock, as in the case of a projectile hitting a target, will disintegrate into fine fragements. A less thorough fragmentation, i.e. a disintegration into larger particles, can be attained through a lesser degree of annealing of the sintered tungsten prior to machining. Thus, the thoroughness of fragmentation can be controlled, within limits, by the degree of annealing and the related recrystalisation of the projectile material.
  • the sintered unalloyed tungsten materials described above have a density of approximately 19 g/cm and their fragmentation characteristics are particularly suited for use in anti-aircraft projectiles ranging in caliber from 12.7 to 40 mm.
  • a fragmentation into larger particles than described above for the smaller calibers is desired. This is accomplished with an approximately 80% dense sintered tungsten subjected to copper infiltration.
  • the thus obtained copper infiltrated tungsten has a density of 16 g/cm 3 .
  • the material Upon impact on an aircraft target, the material disintegrates into randomly shaped fragments having major dimensions from approximately 2 to 8 millimeters.
  • frangible depleted uranium having the relative dynamic strength characteristics for compression and tension described above.
  • Materials of lower density i.e. less than 15 g/cm 3
  • steel alloys, with a density of 7.8 g/cm 3 would have less desirable exterior ballistic and terminal ballistic performances.
  • frangible steel alloys having relative strength characteristics for compression and tension described above would be effective against very fast moving targets such as ICBMs where the net impact velocity is very high.
  • the terminal ballistic mechanism of the frangible tungsten projectile when employed against an essentially aluminium structure such as an aircraft, includes damage due to fragment impact and penetration, pyrophoric reactions and damage induced by aluminium dust and/or aluminium vapor effects.
  • the latter are due to the vaporisation of the aluminium caused by the impacting cluster of high velocity tungsten fragments and the subsequent explosive oxidation of the incandescent aluminium.
  • the extent of the vaporific effects us unique to this type of projectile and is the result of the near total transfer of the kinetic energy of the tungsten fragments to the aluminium target. Being velocity dependent, the magnitude of the terminal effects of the projectile increase with increasing impact velocity.
  • the discarding-sabot, anti-material projectile is also effective against hard armor targets, provided that such targets are the first point of impact. If the projectile is fragmented prior to impacting hard armor, for instance by a sheet of aluminium or other metal installed at a distance ahead of the hard armor, its ability to penetrate the hard armor is reduced.
  • a composite anti-material projectile can be used.
  • a longitudinal cross section depicting the major elements of such a subcaliber projectile 41 is shown in Figure 4.
  • the midsection 41a of the projectile consists of the frangible tungsten alloy described above.
  • the base 41b located at the rear of the projectile is manufactured of a high strength tungsten alloy or equivalent metal commonly used for armor piercing projectiles.
  • pyrophoric material such as zirconium or titanium alloy may be used for the projectile tip 41c.
  • the use of the pyrophoric material is optional and instead the projectile tip 41c may be an extension of the main projectile body 41a and consist of frangible tungsten alloy.
  • Figure 8 illustrates a composite projectile of Figure 4 hitting a multiple plate target.
  • the target includes outer aluminium plates 48 and 50 and an inner armor plate 52.
  • the base 41b of the projectile will remain essentially undeformed and act as an armor-piercing projectile capable of penetrating high strength steel or armored plate 52 within the aircraft structure.
  • a projectile according to the present invention may include a conventional pyrophoric tracer 60 installed at its base as shown in Figure 9.
  • the area surrounding the tracer cavity is desirably reinforced.
  • the presence of the tracer cavity 62 results in substantial shear forces during launch acceleration which can exceed the strength properties of the frangible material.
  • a material combining the properties described earlier has a characteristically low notch sensitivity.
  • the projectile portion containing the tracer cavity 64 is made of a stronger material such as a conventional tungsten alloy, or equivalent.
  • the selection of a high strength tungsten alloy has the advantage the thus reinforced projectile portion 64 can be attached to the forward portion 66 of the projectile by brazing at the common interface 68.
  • the geometric shape of the interface 68 is not critical provided that it does not impose excessive shear loads into the projectile body portion 66 consisting of the frangible material.
  • Self-destruct is the final function of the projectile-borne fuse and is initiated at a certain time of flight corresponding to a range in excess of the effective range of the ammunition.
  • the objective of the self-destruct device is the destruction of projectiles which did not intercept the intended target prior to their impact on friendly soil.
  • a frangible projectile according to this invention has the advantage of requiring neither a fuse nor high explosive filler for its operation.
  • the pyrophoric tracer 60 can be used as a timer to initiate the break-up of the projectile as shown in Figure 10. Break-up is induced by a primer pellet 72 located at the end of the tracer cavity 62. The primer pellet 72 is ignited by the pyrophoric tracer 60 at the end of its burning cycle. The pressure pulse resulting from the combustion of the primer pellet is sufficient to induce the break-up of the frangible projectile body which is already in a prestressed condition due to the spinning motion of the projectile. Subsequent to break-up, the resultant fragments are dispersed and are decelerated by aerodynamic drag to a degree where they cease to be a hazard.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
  • Compositions Of Macromolecular Compounds (AREA)
  • Fats And Perfumes (AREA)
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  • Building Environments (AREA)
  • Polysaccharides And Polysaccharide Derivatives (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
  • Acyclic And Carbocyclic Compounds In Medicinal Compositions (AREA)
  • Steroid Compounds (AREA)
  • Containers And Packaging Bodies Having A Special Means To Remove Contents (AREA)
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  • Reciprocating, Oscillating Or Vibrating Motors (AREA)
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EP81304816A 1980-11-05 1981-10-15 Projectile pour la destruction de matériel militaire Expired EP0051375B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT81304816T ATE40004T1 (de) 1980-11-05 1981-10-15 Geschoss zum vernichten von militaermaterial.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US20187180A 1980-11-05 1980-11-05
US201871 1994-02-25

Publications (3)

Publication Number Publication Date
EP0051375A2 true EP0051375A2 (fr) 1982-05-12
EP0051375A3 EP0051375A3 (en) 1982-09-01
EP0051375B1 EP0051375B1 (fr) 1989-01-11

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP81304816A Expired EP0051375B1 (fr) 1980-11-05 1981-10-15 Projectile pour la destruction de matériel militaire

Country Status (12)

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EP (1) EP0051375B1 (fr)
JP (1) JPS57164299A (fr)
AT (1) ATE40004T1 (fr)
AU (2) AU545632B2 (fr)
CA (1) CA1202210A (fr)
DE (1) DE3176969D1 (fr)
DK (1) DK150257C (fr)
ES (2) ES8303679A1 (fr)
GR (1) GR76297B (fr)
IL (1) IL64115A (fr)
NO (1) NO813733L (fr)
TR (1) TR21751A (fr)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0073385A1 (fr) * 1981-08-31 1983-03-09 GTE Products Corporation Projectile perforant à parties multiples
EP0089000A2 (fr) * 1982-03-11 1983-09-21 Rheinmetall GmbH Projectile à noyau perforant
EP0111712A1 (fr) * 1982-11-18 1984-06-27 Rheinmetall GmbH Projectile sous-calibré à énergie cinétique de grand allongement
US4458599A (en) * 1981-04-02 1984-07-10 Gte Products Corporation Frangible tungsten penetrator
EP0156948A2 (fr) * 1983-10-28 1985-10-09 Rheinmetall GmbH Projectile à calibre réduit, stabilisé par ailettes, de grande proportion longueur/diamètre
FR2619900A1 (fr) * 1987-08-26 1989-03-03 Stribling Gerald Projectile non explosif pour la lutte contre les cibles legeres
US4836108A (en) * 1981-08-31 1989-06-06 Gte Products Corporation Material for multiple component penetrators and penetrators employing same
US4854242A (en) * 1987-05-21 1989-08-08 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Sabot projectile containing a projectile core and a sabot jacket
US4895077A (en) * 1988-05-24 1990-01-23 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Projectile core for a sabot projectile
US4961382A (en) * 1986-05-27 1990-10-09 Motorola, Inc. Penetrating projectile having a self-destructing piercing front end
US4961384A (en) * 1986-02-18 1990-10-09 The United States Of America As Represented By The Secretary Of The Army Hypervelocity penetrator for an electromagnetic accelerator
TR23848A (tr) * 1988-06-25 1990-10-15 N W Kruimpt Gizli
US4970960A (en) * 1980-11-05 1990-11-20 Feldmann Fritz K Anti-material projectile
US4982669A (en) * 1988-02-04 1991-01-08 Rheinmetall Gmbh Subcaliber discarding sabot projectile
US5063854A (en) * 1988-08-16 1991-11-12 Rheinmetall Gmbh Propelling cage discarding sabot for a spin-stabilized subcaliber projectile
DE3532776A1 (de) * 1985-09-13 1992-04-09 Rheinmetall Gmbh Unterkalibriges, drallstabilisiertes mehrzweckgeschoss
WO1998030863A1 (fr) * 1997-01-08 1998-07-16 Geke Ingenieurbüro Projectile ou ogive
EP1780494A2 (fr) * 2005-10-04 2007-05-02 Alliant Techsystems Inc. Projectiles améliorés par l'emploi de matériaux réactifs et procédés
CN114485289A (zh) * 2022-01-11 2022-05-13 宁波大学 反陶瓷复合装甲枪弹

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050199323A1 (en) 2004-03-15 2005-09-15 Nielson Daniel B. Reactive material enhanced munition compositions and projectiles containing same
USRE45899E1 (en) 2000-02-23 2016-02-23 Orbital Atk, Inc. Low temperature, extrudable, high density reactive materials
FR2867469A1 (fr) 2004-03-15 2005-09-16 Alliant Techsystems Inc Compositions reactives contenant un metal, et leur procede de production
IT1400621B1 (it) * 2010-05-13 2013-06-14 Oto Melara Spa Sistema di comunicazione dati ad una spoletta di un'arma da fuoco.

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB538268A (en) * 1939-11-10 1941-07-28 Martin Littmann Improvements in projectiles for military weapons
FR1370967A (fr) * 1962-09-18 1964-08-28 Kohlswa Jernverks Ab Perfectionnements apportés aux projectiles ou analogues du genre de ceux utilisables avec des armes permettant de percer des blindages, et aux procédés pour la réalisation de tels projectiles
US3302570A (en) * 1965-07-23 1967-02-07 Walter G Finch Armor piercing, fragmenting and incendiary projectile
US3370535A (en) * 1959-04-14 1968-02-27 Aviation Uk Armor piercing projectile
CA1009508A (en) * 1974-03-22 1977-05-03 Her Majesty The Queen In Right Of Canada As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government Armour piercing bullets
FR2356906A1 (fr) * 1976-07-01 1978-01-27 Raufoss Ammunisjonsfabrikker Projectile
GB2021739A (en) * 1978-05-24 1979-12-05 Oerlikon Buehrle Ag Spin-stabilised sabot projectile

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2724334A (en) * 1949-12-12 1955-11-22 William C Norton High velocity armor piercing shot
NL106949C (fr) * 1959-01-19

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB538268A (en) * 1939-11-10 1941-07-28 Martin Littmann Improvements in projectiles for military weapons
US3370535A (en) * 1959-04-14 1968-02-27 Aviation Uk Armor piercing projectile
FR1370967A (fr) * 1962-09-18 1964-08-28 Kohlswa Jernverks Ab Perfectionnements apportés aux projectiles ou analogues du genre de ceux utilisables avec des armes permettant de percer des blindages, et aux procédés pour la réalisation de tels projectiles
US3302570A (en) * 1965-07-23 1967-02-07 Walter G Finch Armor piercing, fragmenting and incendiary projectile
CA1009508A (en) * 1974-03-22 1977-05-03 Her Majesty The Queen In Right Of Canada As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government Armour piercing bullets
FR2356906A1 (fr) * 1976-07-01 1978-01-27 Raufoss Ammunisjonsfabrikker Projectile
GB2021739A (en) * 1978-05-24 1979-12-05 Oerlikon Buehrle Ag Spin-stabilised sabot projectile

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4970960A (en) * 1980-11-05 1990-11-20 Feldmann Fritz K Anti-material projectile
US4458599A (en) * 1981-04-02 1984-07-10 Gte Products Corporation Frangible tungsten penetrator
US4836108A (en) * 1981-08-31 1989-06-06 Gte Products Corporation Material for multiple component penetrators and penetrators employing same
EP0073385A1 (fr) * 1981-08-31 1983-03-09 GTE Products Corporation Projectile perforant à parties multiples
EP0089000A2 (fr) * 1982-03-11 1983-09-21 Rheinmetall GmbH Projectile à noyau perforant
EP0089000A3 (en) * 1982-03-11 1983-11-30 Rheinmetall Gmbh Projectile with armour-piercing core
EP0111712A1 (fr) * 1982-11-18 1984-06-27 Rheinmetall GmbH Projectile sous-calibré à énergie cinétique de grand allongement
US4872409A (en) * 1982-11-18 1989-10-10 Rheinmetall Gmbh Kinetic-energy projectile having a large length to diameter ratio
EP0156948A3 (en) * 1983-10-28 1987-07-01 Rheinmetall Gmbh Fin-stabilized subcalibre missile with a high length-to-diameter ratio
US4638738A (en) * 1983-10-28 1987-01-27 Rheinmetall Gmbh. Fin stabilized subcaliber shell of large length to diameter ratio
EP0156948A2 (fr) * 1983-10-28 1985-10-09 Rheinmetall GmbH Projectile à calibre réduit, stabilisé par ailettes, de grande proportion longueur/diamètre
FR2672383A1 (fr) * 1985-09-13 1992-08-07 Rheinmetall Gmbh Projectile sous-calibre a usages multiples, stabilise par rotation.
DE3532776A1 (de) * 1985-09-13 1992-04-09 Rheinmetall Gmbh Unterkalibriges, drallstabilisiertes mehrzweckgeschoss
US4961384A (en) * 1986-02-18 1990-10-09 The United States Of America As Represented By The Secretary Of The Army Hypervelocity penetrator for an electromagnetic accelerator
US4961382A (en) * 1986-05-27 1990-10-09 Motorola, Inc. Penetrating projectile having a self-destructing piercing front end
US4854242A (en) * 1987-05-21 1989-08-08 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Sabot projectile containing a projectile core and a sabot jacket
FR2619900A1 (fr) * 1987-08-26 1989-03-03 Stribling Gerald Projectile non explosif pour la lutte contre les cibles legeres
US4982669A (en) * 1988-02-04 1991-01-08 Rheinmetall Gmbh Subcaliber discarding sabot projectile
US4895077A (en) * 1988-05-24 1990-01-23 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Projectile core for a sabot projectile
FR2765677A1 (fr) * 1988-06-25 1999-01-08 Rheinmetall Gmbh Projectile a effet multiple sous-calibre, stabilise par rotation
TR23848A (tr) * 1988-06-25 1990-10-15 N W Kruimpt Gizli
US5872327A (en) * 1988-06-25 1999-02-16 Rheinmetall Industrie Aktiengesellschaft Subcaliber, spin stabilized multi-purpose projectile
US5063854A (en) * 1988-08-16 1991-11-12 Rheinmetall Gmbh Propelling cage discarding sabot for a spin-stabilized subcaliber projectile
WO1998030863A1 (fr) * 1997-01-08 1998-07-16 Geke Ingenieurbüro Projectile ou ogive
CN1087421C (zh) * 1997-01-08 2002-07-10 盖克工程师事务所 射弹或弹头
US6659013B1 (en) 1997-01-08 2003-12-09 Futurec Ag C/O Beeler + Beeler Treuhand Ag Projectile or war-head
EP1780494A2 (fr) * 2005-10-04 2007-05-02 Alliant Techsystems Inc. Projectiles améliorés par l'emploi de matériaux réactifs et procédés
EP1780494A3 (fr) * 2005-10-04 2008-02-27 Alliant Techsystems Inc. Projectiles améliorés par l'emploi de matériaux réactifs et procédés
CN114485289A (zh) * 2022-01-11 2022-05-13 宁波大学 反陶瓷复合装甲枪弹
CN114485289B (zh) * 2022-01-11 2023-10-10 宁波大学 反陶瓷复合装甲枪弹

Also Published As

Publication number Publication date
TR21751A (tr) 1985-06-03
EP0051375B1 (fr) 1989-01-11
JPS57164299A (en) 1982-10-08
AU7590781A (en) 1982-05-13
ES506852A0 (es) 1983-02-01
DK150257C (da) 1987-10-12
CA1202210A (fr) 1986-03-25
AU545632B2 (en) 1985-07-25
ES8303679A1 (es) 1983-02-01
NO813733L (no) 1982-05-06
ATE40004T1 (de) 1989-01-15
DK150257B (da) 1987-01-19
AU569396B2 (en) 1988-01-28
ES275493Y (es) 1985-01-01
ES275493U (es) 1984-06-01
AU4225585A (en) 1985-09-05
JPS6144240B2 (fr) 1986-10-01
GR76297B (fr) 1984-08-04
EP0051375A3 (en) 1982-09-01
DE3176969D1 (en) 1989-02-16
DK488481A (da) 1982-05-06
IL64115A (en) 1986-03-31

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