WO1987007708A1 - Projectile transpersant un blindage - Google Patents

Projectile transpersant un blindage Download PDF

Info

Publication number
WO1987007708A1
WO1987007708A1 PCT/GB1986/000329 GB8600329W WO8707708A1 WO 1987007708 A1 WO1987007708 A1 WO 1987007708A1 GB 8600329 W GB8600329 W GB 8600329W WO 8707708 A1 WO8707708 A1 WO 8707708A1
Authority
WO
WIPO (PCT)
Prior art keywords
projectile
carrier
core
target
leading edge
Prior art date
Application number
PCT/GB1986/000329
Other languages
English (en)
Inventor
Abraham Flatau
Original Assignee
Royal Ordnance Pld
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
Priority to US06/743,879 priority Critical patent/US4612860A/en
Application filed by Royal Ordnance Pld filed Critical Royal Ordnance Pld
Priority to DE8686903516T priority patent/DE3671100D1/de
Priority to JP61503426A priority patent/JPH01500611A/ja
Priority to AT86903516T priority patent/ATE52612T1/de
Priority to EP86903516A priority patent/EP0270527B1/fr
Priority to PCT/GB1986/000329 priority patent/WO1987007708A1/fr
Priority to IN538/DEL/86A priority patent/IN167008B/en
Priority to KR870700375A priority patent/KR880700921A/ko
Priority to DK288487A priority patent/DK164930C/da
Priority to NO87874568A priority patent/NO164131C/no
Publication of WO1987007708A1 publication Critical patent/WO1987007708A1/fr

Links

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
    • 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

Definitions

  • the invention relates to projectiles, and more specifically to armour penetrating projectiles which contain therein penetrator cores.
  • sabots were designed to encapsulate the rod penetrator during handling, storage and gun firing, and to discard shortly after exiting the muzzle, thus allowing only the rod penetrator to continue in flight toward the target.
  • the sabot discard process can introduce trajectory inaccuracies for the rod projectile, as well as representing a mass-energy loss.
  • SUBSTITUTESHEET It is an object of the invention to provide an armour piercing projectile which overcomes the problems set forth in detail herein above by retaining all of the in-bore projectile components, and which are designed to contribute to the process of target penetration.
  • a composite projectile adapted to be fired from a gun bore to penetrate armour protected targets includes a rigid hollow carrier having an open forward-facing front end and a rear end relative to the direction of projectile movement toward a target surface, said carrier having an annular non-deformable leading edge at said front end, a penetrator core being adapted to fit in slidable relationship within said carrier and restrained within said carrier by a restraining member of said carrier whereby said penetrator is able to slide out of said carrier at its front end but not at its rear end, said core having a front end which is adapted to penetrate an armoured target and which, when said projectile is fired, is situated within said carrier aft of the leading edge of said carrier.
  • the projectile according to the present invention provides improved penetration of armoured targets, surprisingly without necessarily requiring the use of discarding components, in the unique manner described below by which both the carrier and the penetrator core contribute to the penetration process.
  • the carrier is elongate and substantially cylindrical and has a sharp annular leading edge.
  • the leading edge may be provided by a bevel on one or both of the inner and outer
  • the rear end of the carrier may be tapered to reduce aerodynamic drag.
  • the rear end of the core may be similarly tapered to be conveniently accommodated within the carrier.
  • the said restraining member may be a wall or collar defining the end of the bore into which the said penetrator core slidably fits.
  • the rear end of the carrier may itself be closed and thereby provide the wall which acts as the restraining member.
  • the penetrator core may be restrained in direct contact with the wall or by one or more intermediate members located between the wall and the core, e.g. as described further below.
  • the penetrator core has a tapered front end which desirably terminates in a point.
  • the taper may be provided as a single conical section or alternatively as a plurality of conical sections of different taper angle providing a gradual convergence to the front of the core of the profile of the core as seen in cross-section.
  • the front end of the core may however be an annular, preferably sharp, non-deformable leading edge.
  • the core may be tubular or partly tubular and may include within the bore of the tubular portion a further member, slidably located in the bore.
  • Such a member may itself provide a contribution to the target penetration process.
  • it may, upon firing, have a front end which is situated behind the front end of the body of the core whereby penetration of the target is provided in a three-stage process by the carrier, core body and further member slidably fitted in the core body.
  • the further member may have any of the forms described above which the core itself may have as a unitary structure.
  • the front end of the core may, for example, be situated approximately level with or behind the beginning of a bevel providing the leading edge of the carrier when the projectile is fired from a gun.
  • the core is preferably made at least in part of a high density material adapted to penetrate armour, e.g. of a tungsten alloy or depleted uranium. Such materials are well known per se to those skilled in the art.
  • the front end of the core may be made of the said high density material although the front end may additionally include a tip of lighter material, e.g.- steel, designed to provide greater initial penetration of a target surface as is known to those skilled in the art.
  • the projectile according to the present invention additionally includes a nose secured to the carrier at or adjacent to its front end.
  • a nose which is preferably a fairing comprising a conical or rounded ogival thin-walled hollow structure, is adapted to serve as a shield reducing aerodynamic drag of the projectile during flight toward a target.
  • the nose which may be made of a lightweight material such as a plastics material or an aluminium alloy, is readily disintegrated upon striking a target. Carried material, e.g. incendiary or other material, may be enclosed in the cavity within the nose.
  • the carrier of the projectile according to the present invention may be formed of a single material, e.g. high strength steel, although it may alternatively comprise a plurality of dissimilar materials.
  • a forward material e.g. high strength steel
  • a forward force e.g. a forward force
  • a forward force e.g. a forward force
  • a forward force e.g. a forward force
  • SUBSTITUTE SHEET portion including the leading edge of the carrier may be made of a high strength, high hardness material, e.g. high strength steel, while a rear portion may be made of a lighter material such as an aluminium alloy or a fibre reinforced composite material.
  • a lighter material such as an aluminium alloy or a fibre reinforced composite material.
  • Many such composite materials are well known to those skilled in the engineering materials art and may for example comprise fibres selected from one or more of carbon, boron, glass, aramid, metal, high strength plastics such as polyolefin embedded in a suitable matrix such as a thermosetting or a thermoplastic resin or a ceramic or metal.
  • the dissimilar portions of the carrier may be attached together by any suitable technique well known in the engineering art, e.g. by .screw threads or adhesive bonding.
  • the resulting carrier so formed comprises a srngle solid substantially cylindrical hollow mass.
  • the penetrator core in the projectile according to the invention may, when fitted in the carrier for firing, contact directly the inner wall of the closed rear end of the carrier.
  • the rear end of the carrier and the penetrator core may be separated by an intermediate member.
  • a slug may be provided behind the penetrator core.
  • Such a slug may be made of material which is heavier than the penetrator core and which provides a greater impact force to the core when it strikes a target surface.
  • the slug may comprise a capsule containing a carried material, e.g. a chemical agent, an explosive material, an incendiary material which scatters within a crew-compartment or the like after penetration. The outside of such a capsule may for example
  • SUBSTITUTESHEET comprise a crushable plastics material or a composite or metal wall.
  • the core may conveniently be shaped at its rear end to receive the slug, e.g. by including a depression such as a spherical or conical cavity into which the slug rests.
  • the carrier especially in its rear end, may carry a tracer, e.g. any of the tracers well known to those skilled in the art.
  • the entire armour piercing projectile of this invention is designed to remain integral when fired from a gun. Retaining the carrier and designing it to be utilised to initiate the penetration process prior to the impact of the rod core has heretofore never been undertaken and successfully achieved.
  • the benefit of improved penetration obtained by the composite projectile of the invention can however still be achieved even if the present composite projectile is itself a sub-calibre component of a larger round which could, for example, include a discarding sabot or other component.
  • the projectile according to the invention may be provided with any suitable means known to those skilled in the art to engage the rifled barrel of a gun in order to impart to the projectile rotational torque to provide suitable in-flight stability.
  • the gun from which the projectile according to the present invention is fired may comprise a small arms weapon, e.g. having a calibre up to 20mm, a medium calibre weapon e.g. in calibres from 20mm to 60mm, or a heavy weapon e.g. having a calibre greater than 60mm, although the invention
  • SUBSTITUTESHEET is likely to find most use in small arms and medium calibre applications.
  • Figure 1 is a cross-sectional view of one embodiment of this invention.
  • Figure 2 is a cross-sectional view of a second embodiment of this invention.
  • Figure 3 is a cross-sectional view of a prior art non-saboted high density core .50 inch calibre (12.7mm) projectile currently used;
  • Figure 4 is a cross-sectional view of the currently used prior art Air Force GA ⁇ -8 30mm high density core projectile
  • FIG. 5 is a cross-sectional view of the prior art Armour Piercing Discarding Sabot (APDS) Projectile as currently used in gun systems such as the 20mm Phalanx;
  • APDS Armour Piercing Discarding Sabot
  • Figure 6 is a longitudinal view schematically illustrating the initiation of the penetration process as the projectile embodying the invention impacts the target;
  • Figure 7 is a longitudinal view schematically illustrating the continuation of the penetration process shown in Figure 6;
  • Figure 8 is a cross-sectional view of a third embodiment of this invention.
  • Figure 9 is a cross-sectional view of a fourth embodiment of this invention.
  • Figure 10 is a longitudinal view illustrating the initiation of the penetration process as the prior art currently used non-saboted high density core projectile impacts a target;
  • Figures 11 to 15 are cross-sectional views of various penetrator cores in further alternative embodiments of the invention.
  • a full-calibre projectile embodying the present invention has an outward shape and symmetry very similar to those of conventional projectiles, providing an advantage not heretofore obtained with known discarding sabot projectiles.
  • Major components or parts of this new projectile 10 include an elongate carrier 11, which may be made of steel, an elongate rod penetrator core 12, made of high density material such as tungsten alloy or depleted uranium, and a thin ogival nose shield 13 attached to the forward end of the carrier 11.
  • the nose shield 13 may be made of plastics or aluminium, but in any case is preferably light in weight.
  • the core 12 has a front end in the form of a pointed nose 14 which is not aligned in a vertical plane with a beveled leading edge 15 of the carrier 11. Rather, the core nose 14 is deliberately placed aft or behind the leading edge 15 of carrier 11 with reference to the travel direction 25 of projectile 10.
  • the front of the nose 14 is approximately level with the start of the bevel providing the sharp leading edge 15 upon firing from a gun (not shown) . This relative positioning is done to produce the following sequence of events and is based on the phenomena of interaction between the projectile 10 and the surface of impact.
  • the sharp, annular beveled leading edge 15 of the carrier 11 produces a stress field in a target 50 as shown in Figure 6. As the stress waves meet in the target material, they combine and result in a wave
  • the stress field initiated by the beveled leading edge 15 of the carrier 11 is thereby supplemented by a second series of shock loading stresses concentrated in the same field, the overall effect being in the manner of a "one-two punch" which is far more damaging than a single punch by either penetration mechanism acting alone.
  • FIG. 2 The projectile shown in Figure 2 is similar in geometry to the projectile of Figure 1, except that the Figure 2 embodiment has been adapted to include an incendiary material 16 located inside the shield 13 and enclosed by the rod penetrator core 12 and the forward section of the carrier 11. It will be recognised that either , embodiment. Figure 1 or Figure 2, could readily include a known tracer (not shown) in the base- of the carrier body as will be readily apparent to those skilled in the art.
  • Figure 3 depicts a prior art .50 inch calibre (12.7mm) conventional anti-armour projectile 20 in current use. It consists of a high density material core 21 placed within an aluminium base Carrier 22. The forward section of the projectile incorporates either a filler material such as a' plaster or an incendiary material 23. The entire structure is encased by a thin gilding metal envelope 24. In contrast to the present invention, the only element of prior art projectile 20 involved in the target penetration process is the core 21.
  • the invention may be utilised in a wide range of guns, from handguns through to larger calibre guns and the projectile shape and size will vary according to the application. However, the same beneficial penetration phenomena discussed above with reference to Figures 6 and 7 will apply in the case of the geometric envelope of each specific projectile size or configuration. As an example of the range of different projectiles in current use, although the current .45 inch calibre (11.4mm) round has a short projectile length to diameter ratio, it is primarily intended for
  • the present 30mm GAU-8 projectile envelope, shown in Figure 4 allows for a much greater projectile length to diameter ratio, which then provides for a longer rod core, giving more mass and a higher ballistic coefficient for target penetration. This is entirely appropriate as the larger calibre projectiles are intended for anti-material purposes.
  • the present GAU-8 anti-armour projectile 30 shown in Figure 4 consists of a high density material rod core 21 surrounded by an aluminium material 32 which forms the projectile configuration. Upon target impact, an aluminium windscreen 33 is readily broken up leaving the high density rod 31 to penetrate the target. This action produces only a* single stage penetration stress pattern and is not capable of defeating heavy armour plate systems.
  • the projectiles embodying the present invention may have an overall shape similar to that of these known projectiles .
  • Figure 5 represents a form of the current discarding sabot projectile as patented by Feldman (United States Patents Nos. 3,714,900 and 3,905,299).
  • sabot elements 42, 43 and windshield 44 must be discarded after leaving the gun muzzle (not shown) in order to allow the sub-calibre core 41 to continue toward the target without the considerable ballistic drag which would result from failure to discard such components.
  • gun muzzle not shown
  • the sabot must totally discard all
  • SUBSTITUTESHEET its parts in a matter of micro-seconds, immediately when the round exits the gun muzzle, and without any angular or lateral non-symmetrical forces applied to the core 41 such as would disrupt its uninhibited trajectory even slightly. Any such aerodynamic perturbations during discard could cause the penetrator to miss the distant target or to alter its angularity at impact, which degrades its penetration effectiveness away from optimum design conditions.
  • the projectiles embodying this invention need not have discarding dead-weight, high drag masses or parasitic elements which do not contribute to the penetration process, and their accuracy need not be compromised by highly sensitive and unreliable sabot-discarding mechanisms.
  • FIG. 8 a further embodiment of the present invention is seen for use where gun recoil and barrel forces are limited within a narrow performance force envelope, and excessive impulse loading could destroy the weapon by using projectiles having a higher mass than that the gun is designed to fire.
  • a decrease in projectile mass may be desirable. Therefore, in the embodiment shown in Figure 8, this is accomplished by forming the carrier 11 in two parts instead of a single unitary mass as shown in Figure 1.
  • the Figure 8 modification shows carrier 11 comprising two structurally joined portions 26 and 18 made from two dissimilar materials. Forward portion 26 formed with the forward sharply beveled leading edge 15 is made of undeformable and high-hardness material such as high-strength steel, while aft or rear portion 18 is made of-
  • SUBSTITUTESHEET lighter weight material such as aluminium, reinforced plastics or strong and lightweight composite fiberglass or filament laminates of metallic, ceramic and non-metallic materials.
  • Elements 26 and 18 are securely joined at their interface 19 by any suitable means such as screw-threads, various high-strength epoxy based adhesives, or any other assembly techniques known to the prior art and widely used in industry. When thus joined, elements 26 and 18 form a single solid, substantially cylindrical hollow mass which is dimensioned so as to grasp snugly the heavier and higher density penetration core 12 in the same manner that carrier 11 embraces and retains the core 12 in Figure 1.
  • Figure 9 shows a further modification of the inventive structure.
  • the mass slidably located inside the carrier 11 instead of being a simple homogeneous core 12 as in Figure 1, is composed of plural elements consisting of a front core 12 and a rear element 17.
  • the core 12 has a generally conical pointed nose 14 and is made from high density, non-deforming material which may be the same as the materials discussed above for the core 12 shown in Figure 1.
  • Element 17 behind the core 12 is of material different from the core 12, however, and may be heavier or lighter, depending upon the combat needs which the round is designed to fulfil.
  • the element 17 may be an elongate slug of material heavier than core 12, and may be positioned so as to add greater impact force to assist the core 12 at the time projectile 10 strikes a target surface.
  • the core 12 shown in Figure 9 is provided with a depression such as a spherical or conical cavity at its aft
  • the element 17 has either a spherical or conical forward end portion which nests or bears against the aft cavity in core 12 as shown in Figure 9 in a symmetrical pattern of surface bearing contact.
  • the element 17 may, alternatively, comprise a crrishable plastics, composite, or metallic capsule containing a carried material. The precise composition of the carried material will depend upon the combat need to be served.
  • the element 17 may for example comprise a chemical agent, an explosive material, or an incendiary material which scatters within a crew compartment or the like after penetration is achieved by the carrier 11 and the core 12.
  • the penetrator core 12 has a pointed nose 14.
  • the nose 14 is shown in each case as being of the same material as the body of the core 12 although it could have a tip of different material, e.g. steel where the core " 12 body is of tungsten alloy or depleted uranium.
  • the core 12 is tubular and the leading edge 64 is provided by beveled surfaces 65 on the inside and outside of the tube.
  • the shape of the core 12 is similar to that shown in Figure 11 except that only a front portion 66 of the core 12 is tubular.
  • the core 12 in this case has a rear portion 67 which is solid. As shown, the rear
  • SUBSTITUTESHEET portion 67 may be of different material,- e.g. heavier material, than that of the front portion 66.
  • the shape is similar to that shown in Figure 11.
  • the tubular core 12 additionally contains a rod 68 slidably fitted within the core 12.
  • the rod 68 is, upon firing of the projectile, set back within the bore of the core 12 in the same manner that the core 12 is itself set back within the carrier
  • the carrier 11, tubular core 12 and rod 68 serve in this case to provide a three stage target penetration process instead of the two stage process described with reference to Figure 7.
  • the'annular leading edge 64 is provided at the front of a conical portion 69, the edge 64 being sharply formed by a slot 61 machined in the front of the core ' 12.
  • Figure 15 is similar to that shown in Figure 14 except that in Figure 15 the body of the core 12 is tubular. In a similar alternative embodiment (not shown) to that shown in Figure 15 the rear end only of the core
  • the core 12 is to be fitted in its carrier 11 in the manner shown in Figure 1 and a nose 13 is to be fitted on the front of the carrier 11, also as shown in Figure 1.
  • the cavity inside the nose 13 may be used for loading useful carrier material other than incendiary material (as mentioned).
  • the carrier e.g. carrier 11
  • the carrier may include any suitable means to engage the rifled barrel of a gun to impart the necessary rotational torque, e.g. a driving band or pusher/obturator may be used as will be apparent to those skilled in the art.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Non-Silver Salt Photosensitive Materials And Non-Silver Salt Photography (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Glass Compositions (AREA)
  • Metal-Oxide And Bipolar Metal-Oxide Semiconductor Integrated Circuits (AREA)
  • Electromagnets (AREA)
  • Reciprocating, Oscillating Or Vibrating Motors (AREA)
  • Cosmetics (AREA)
  • Compositions Of Macromolecular Compounds (AREA)
  • Table Devices Or Equipment (AREA)

Abstract

Projectile (10) transpersant un blindage, possédant un corps de support (11) et un noyau (12) de pénétration de préférence de densité élevée. La partie de bord d'attaque (15) du corps de support (12) est de préférence biseautée et s'étend au-delà de l'extrémité avant (14) du noyau de pénétration. Le corps de support (12) est de préférence entouré d'un élément pointu (13) assurant une traînée aérodynamique relativement faible pendant le vol. Le corps de support est conçu de manière à permettre au projectile d'être stabilisé par sa rotation sur son axe longitudinal, lorsqu'il est tiré par une arme appropriée.
PCT/GB1986/000329 1984-07-02 1986-06-09 Projectile transpersant un blindage WO1987007708A1 (fr)

Priority Applications (10)

Application Number Priority Date Filing Date Title
US06/743,879 US4612860A (en) 1984-07-02 1985-06-12 Projectile
DE8686903516T DE3671100D1 (de) 1986-06-09 1986-06-09 Panzerbrechendes geschoss.
JP61503426A JPH01500611A (ja) 1986-06-09 1986-06-09 発射体
AT86903516T ATE52612T1 (de) 1986-06-09 1986-06-09 Panzerbrechendes geschoss.
EP86903516A EP0270527B1 (fr) 1986-06-09 1986-06-09 Projectile transpersant un blindage
PCT/GB1986/000329 WO1987007708A1 (fr) 1986-06-09 1986-06-09 Projectile transpersant un blindage
IN538/DEL/86A IN167008B (fr) 1986-06-09 1986-06-18
KR870700375A KR880700921A (ko) 1986-06-09 1987-04-29 발 사 체
DK288487A DK164930C (da) 1986-06-09 1987-06-04 Projektiler
NO87874568A NO164131C (no) 1986-06-09 1987-11-03 Prosjektil.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/GB1986/000329 WO1987007708A1 (fr) 1986-06-09 1986-06-09 Projectile transpersant un blindage

Publications (1)

Publication Number Publication Date
WO1987007708A1 true WO1987007708A1 (fr) 1987-12-17

Family

ID=10591039

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1986/000329 WO1987007708A1 (fr) 1984-07-02 1986-06-09 Projectile transpersant un blindage

Country Status (9)

Country Link
EP (1) EP0270527B1 (fr)
JP (1) JPH01500611A (fr)
KR (1) KR880700921A (fr)
AT (1) ATE52612T1 (fr)
DE (1) DE3671100D1 (fr)
DK (1) DK164930C (fr)
IN (1) IN167008B (fr)
NO (1) NO164131C (fr)
WO (1) WO1987007708A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1521052A1 (fr) * 2003-10-03 2005-04-06 Giat Industries Munition perforante
WO2007022838A1 (fr) * 2005-08-24 2007-03-01 Rwm Schweiz Ag Projectile, notamment pour des munitions de moyen calibre
DE19730968B4 (de) * 1996-08-14 2013-09-05 Lapua Oy Verfahren zur Herstellung eines Geschosses und Geschoß
US9404721B2 (en) 2007-07-26 2016-08-02 Kimball Rustin Scarr Ring airfoil glider with augmented stability

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE443242T1 (de) * 2004-05-11 2009-10-15 Ruag Ammotec Bleifreies geschoss

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR333930A (fr) * 1903-07-06 1903-12-07 Deutsche Waffen & Munitionsfab Perfectionnements aux projectiles
GB572732A (en) * 1941-10-03 1945-10-22 William Mosey Improvements in or relating to armour piercing bullets
US3302570A (en) * 1965-07-23 1967-02-07 Walter G Finch Armor piercing, fragmenting and incendiary projectile
FR2356906A1 (fr) * 1976-07-01 1978-01-27 Raufoss Ammunisjonsfabrikker Projectile
US4108073A (en) * 1975-02-27 1978-08-22 The United States Of America As Represented By The Secretary Of The Air Force Armor piercing projectile
US4435887A (en) * 1981-03-27 1984-03-13 A/S Raufoss Ammunisjonsfabrikker Method of making projectile

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5144360A (ja) * 1974-10-14 1976-04-15 Hitachi Ltd Dennetsuheki

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR333930A (fr) * 1903-07-06 1903-12-07 Deutsche Waffen & Munitionsfab Perfectionnements aux projectiles
GB572732A (en) * 1941-10-03 1945-10-22 William Mosey Improvements in or relating to armour piercing bullets
US3302570A (en) * 1965-07-23 1967-02-07 Walter G Finch Armor piercing, fragmenting and incendiary projectile
US4108073A (en) * 1975-02-27 1978-08-22 The United States Of America As Represented By The Secretary Of The Air Force Armor piercing projectile
FR2356906A1 (fr) * 1976-07-01 1978-01-27 Raufoss Ammunisjonsfabrikker Projectile
US4435887A (en) * 1981-03-27 1984-03-13 A/S Raufoss Ammunisjonsfabrikker Method of making projectile

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19730968B4 (de) * 1996-08-14 2013-09-05 Lapua Oy Verfahren zur Herstellung eines Geschosses und Geschoß
EP1521052A1 (fr) * 2003-10-03 2005-04-06 Giat Industries Munition perforante
EP1701131A2 (fr) 2003-10-03 2006-09-13 Giat Industries Munition perforante
EP1701131A3 (fr) * 2003-10-03 2006-10-04 Giat Industries Munition perforante
WO2007022838A1 (fr) * 2005-08-24 2007-03-01 Rwm Schweiz Ag Projectile, notamment pour des munitions de moyen calibre
US9404721B2 (en) 2007-07-26 2016-08-02 Kimball Rustin Scarr Ring airfoil glider with augmented stability
US10890422B2 (en) 2007-07-26 2021-01-12 Scarr Research and Development Co., LLC Ring airfoil glider with augmented stability

Also Published As

Publication number Publication date
DK288487D0 (da) 1987-06-04
IN167008B (fr) 1990-08-18
JPH01500611A (ja) 1989-03-01
KR880700921A (ko) 1988-04-13
EP0270527B1 (fr) 1990-05-09
NO874568L (no) 1987-12-17
DK164930C (da) 1993-01-25
NO164131C (no) 1990-08-29
NO164131B (no) 1990-05-21
ATE52612T1 (de) 1990-05-15
NO874568D0 (no) 1987-11-03
DE3671100D1 (de) 1990-06-13
DK288487A (da) 1987-12-17
DK164930B (da) 1992-09-07
EP0270527A1 (fr) 1988-06-15

Similar Documents

Publication Publication Date Title
US4612860A (en) Projectile
US4108072A (en) Armor-piercing projectile having spaced cores
KR100220883B1 (ko) 수중 물체에 사용하기 위한 공기 역학적으로 안정화된 발사체 시스템
US4517898A (en) Highly accurate projectile for use with small arms
US4597333A (en) Two-part armor-piercing projectile
US8096243B2 (en) High velocity ammunition round
US7568433B1 (en) Aerodynamically stable finless projectile
US3905299A (en) Discarding sabot projectiles
US4075946A (en) Armor piercing projectile
US4653404A (en) High velocity notched ammunition sabot
US5297492A (en) Armor piercing fin-stabilized discarding sabot tracer projectile
US4649829A (en) Plastic armor piercing projectile
US4878432A (en) Multistage kinetic energy penetrator
US4805535A (en) Projectile
US6662726B1 (en) Kinetic energy penetrator
CZ287507B6 (en) Ammunition for a weapon of small, medium or great caliber
CA3035079A1 (fr) Projectile muni d'un penetrateur
US9677863B1 (en) Long rod penetrator concept for small caliber munitions
US4823703A (en) Armor penetrating and self-lubricating projectile
EP0270527B1 (fr) Projectile transpersant un blindage
US5092246A (en) Small arms ammunition
US5014931A (en) Kinetic energy projectile with impact-ejected fins
US4961384A (en) Hypervelocity penetrator for an electromagnetic accelerator
NO171812B (no) Underkaliber-underspeilprosjektil
JP3575831B2 (ja) 縮射用翼安定徹甲弾の速度低下の低減

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AU BR DK JP KR NO

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH DE FR GB IT NL SE

WWE Wipo information: entry into national phase

Ref document number: 1986903516

Country of ref document: EP

WWP Wipo information: published in national office

Ref document number: 1986903516

Country of ref document: EP

WWG Wipo information: grant in national office

Ref document number: 1986903516

Country of ref document: EP