EP0088999B1 - Projectile à noyau perforant pour combattre des armures multicouches - Google Patents

Projectile à noyau perforant pour combattre des armures multicouches Download PDF

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Publication number
EP0088999B1
EP0088999B1 EP83102300A EP83102300A EP0088999B1 EP 0088999 B1 EP0088999 B1 EP 0088999B1 EP 83102300 A EP83102300 A EP 83102300A EP 83102300 A EP83102300 A EP 83102300A EP 0088999 B1 EP0088999 B1 EP 0088999B1
Authority
EP
European Patent Office
Prior art keywords
core element
projectile
casing
core
elements
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.)
Expired
Application number
EP83102300A
Other languages
German (de)
English (en)
Other versions
EP0088999A2 (fr
EP0088999A3 (en
Inventor
Hans Werner Luther
Jürgen Winkelmann
Patrick Montier
Jean-Claude Sauvestre
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.)
Rheinmetall Industrie AG
Direction General pour lArmement DGA
Original Assignee
Rheinmetall GmbH
Direction General pour lArmement DGA
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 Rheinmetall GmbH, Direction General pour lArmement DGA filed Critical Rheinmetall GmbH
Priority to AT83102300T priority Critical patent/ATE27487T1/de
Publication of EP0088999A2 publication Critical patent/EP0088999A2/fr
Publication of EP0088999A3 publication Critical patent/EP0088999A3/de
Application granted granted Critical
Publication of EP0088999B1 publication Critical patent/EP0088999B1/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
    • F42B12/04—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 a sub-caliber arrow-stabilized armor-piercing bullet with the features of the preamble of claim 1.
  • a projectile of the type mentioned is known from DE-C-14 28 679. It has different armor-piercing pre-core elements in an envelope axially one behind the other and an armor-piercing main core element adjoining the rear thereof. Between the core elements, which consist of hard and / or heavy metal, layers of plastic-bonded hollow spheres or a light metal alloy are provided as shock-absorbing means. By arranging the different core elements, a targeted mass cultivation of the storey arrangement is to be realized in such a way that after penetration of pre-armor while protecting the main core element against premature destruction due to shock wave stress against a main armor of the target, a sufficient mass of mass is still available in the form of the main core element.
  • missiles of the type mentioned at the outset are exposed to loads acting when penetrating multi-plate targets transverse to the longitudinal axis of the projectile, which regularly lead to premature bending of the missile.
  • a penetration channel inclined towards the extension of the projectile trajectory can prevent the main core element from reaching the main armor and thus impair the effect of the projectile in a very sensitive manner.
  • the invention is therefore based on the object of improving a projectile of the type mentioned in such a way that, while avoiding premature bending fracture, in particular of the main core element, extensive use of the energy inherent in the projectile to combat multi-plate targets is achieved, and the missile without any fundamental structural changes each target is customizable.
  • balancing projectiles which consist of core elements, the adjacent ends of which are essentially articulated. From these arrangements, however, there is no indication of the configuration of a wing-stabilized, so-called long storey, large length-diameter ratio in the sense of the above-mentioned task. According to these references, a pivoting movement is to be transmitted from a front core element to a rear core element in order to give the rear element a different direction. In contrast, the present application is only intended to prevent the rear core element from being pressed out or broken from its direction.
  • FIGS. 1 to 5 The drawing shows in FIGS. 1 to 5 embodiments of respective tip areas of the new projectile in section parallel to the longitudinal axis.
  • a first embodiment has a first pre-core element 10 in the tip region and a second pre-core element 20 which is axially arranged downstream thereof and to which a main core element 30 is connected at the rear.
  • a front surface 12 of the pre-core element 10 is designed as a hemispherical surface. It runs on the back into a circular cylindrical peripheral surface 18.
  • a rear side surface 14 of the front core element 10 is designed as a hollow spherical cap, to which an annular surface 16 adjoins in the peripheral region and which crosses a longitudinal axis A of the projectile.
  • a front surface 22 of the pre-core element 20 is designed as a hemispherical surface which is delimited in the base-side circumferential area by an annular surface 24. Between the mutually facing circular ring surfaces 16 and 24 there is an axial distance, not specified, which is to be assigned to a first intermediate region 40.
  • a circular cylindrical peripheral surface 21 of the pre-core element 20 is of the same diameter as the peripheral surface 18.
  • a rear surface 26 of the pre-core element 20 is designed as a hollow spherical cap and is delimited in the circumferential area by an annular surface 28 crossing the longitudinal axis A of the projectile.
  • a main core element 30 adjoining on the rear is adapted with its front surface 32 to the rear surface 26 and is delimited in the peripheral region by an annular surface 34 crossing the longitudinal axis A of the projectile.
  • An axial distance, not specified, between the mutually facing circular ring surfaces 28 and 34 is to be assigned to a second intermediate area 42.
  • a sleeve 36 extends axially over the two pre-core elements 10 and 20 and a front region of the main core element 30, which area is not specified, and tightly encloses them.
  • a tip element 46 with a hemispherical head 48 is fixed with a circular cylindrical bolt 50 in a central axial bore 52.
  • a second exemplary embodiment differs from that according to FIG. 1 by the formation of a rear surface 27 of the front core element 20 and a front surface 33 of the main core element 30.
  • the latter is circular-conical and the former funnel-shaped designed, the surfaces 27 and 33 touch each other.
  • the pre-core element 10 has a first circular-cylindrical region 10 'and a second circular-cylindrical region 10 "of comparatively larger diameter adjoining the rear.
  • the circumferential surface 18 of the region 10 is delimited on the back by a narrow truncated cone surface 16 ", over which a circular cylindrical region 10'" projects, which continues in a rear part with a hemispherical surface 14 '.
  • the pre-core element 20 is adapted with a front hollow spherical surface 22 "of the hemispherical surface 14' and is delimited in the circumferential area by an annular surface 24 crossing the longitudinal axis A of the projectile.
  • the peripheral surface 21 is of the same diameter as the peripheral surface 18.
  • the front core element 20 is delimited on the back by a circular conical surface 27 ′′.
  • An axial distance between the surfaces 16 ′′ and 24, which is not specified in any more detail, is to be assigned to a first intermediate region 40. With its funnel-shaped front surface 33 '- it is delimited by a circumferential annular surface 34' - the main core element 30 is adapted to the pre-core element 20.
  • a circular cylindrical region 39 has an external thread 39 ', to which a groove 31 is connected on the rear.
  • the casing 36 extends from a rear edge 37 'in the immediate vicinity of an internal thread, not corresponding to the external thread 39', to the ballistic hood 44.
  • a second intermediate region 42 is essentially defined by the surfaces 27 "and 33 'and the thread 39 ', while a predetermined breaking point 38 designed as a wall weakening of the shell 36 is arranged in the first intermediate region 40.
  • the shell 36 extends with essentially the same wall thickness over the region 10 "of the pre-core element 10 and points in the vicinity of the region 10 'A reinforcement 45 with a circular cylindrical inner surface 45' of smaller inner diameter.
  • the reinforcement 45 can already be assigned to a ballistic hood 44, the tip design of which corresponds to that of the aforementioned exemplary embodiments.
  • the screw connection of the casing 36 to the main core element 30 advantageously allows one or both of the pre-core elements 10, 20 to be exchanged, for example to adapt to a particular target to be combated.
  • a pre-core element 10 in turn has two circular cylindrical regions 10 ′, 10 ′′ of different diameters.
  • the latter is delimited by a rear surface 14 designed as a hollow spherical cap with a circumferential annular surface 16 that crosses the longitudinal axis A of the floor 14, a hemispherical damping element 54 is fitted on the front side.
  • a pin formed in this way protrudes over an annular surface 24 ', the peripheral region of which is not covered by the damping element 54.
  • An axial distance between the surfaces 16 and 24, like the damping element 54, is to be assigned to a first intermediate region 40 '.
  • the front core element 20 is bounded on the back by a circular funnel surface 27, to which a damping element 56 is adapted.
  • the latter is designed in the shape of a circular funnel with a predetermined wall thickness and is adapted on the back to a circular conical surface 33 of the main core element 30.
  • the damping element 56 is to be assigned to a second intermediate area 42 ′, while a predetermined breaking point 38 formed as a wall weakening of the casing 36 is included in the first intermediate area.
  • the pre-core element 10 has a hemispherical front surface 12 and a central rear surface 14 'which crosses the longitudinal axis A of the projectile.
  • a circular cylindrical surface 15 projects beyond the latter and is delimited in the peripheral region by an annular surface 16 '.
  • a damping element 58 is adapted with a front region of the rear side 14 ', 15, 16' of the front core element 10, which is not specified in any more detail, and is delimited on the rear side by a surface 58 'in the form of a spherical cap, which is adjoined on the circumference by a circular ring surface 60 which crosses the longitudinal axis A of the projectile .
  • the pre-core element 20 is designed essentially circular-cylindrical, the circular-cylindrical region being delimited by a circular ring surface 24 on the front and a circular ring surface 25 on the rear. Over the former is a spherical cap with a front surface 22 which is adapted to the surface 58 'of the damping layer 58. An axial distance, not specified, between the circular ring surfaces 60 and 24 is to be assigned to a first intermediate region 40 '. A hemispherical part with a rear surface 26 'protrudes beyond the rear circular surface 25. With a predetermined axial distance, a front region of the main core element 30 adjoins with a surface 32, formed in mirror image.
  • the damping element 62 is designed on the tip side in accordance with the exemplary embodiments described above.
  • an advantageous mass ratio of 1: 1.2: 6 should be pointed out, in connection with a corresponding arrangement the first numerical value of the first pre-core element 10, the second numerical value of the pre-core element 20 and the third numerical value is assigned to the main core element 30.
  • the main core element 30 is preferably made of a high-strength, ductile heavy metal alloy, for example a sintered alloy with a high tungsten content, while the two pre-core elements consist of a corresponding material with lower ductility. If damping elements are used, however, the first pre-core element 10 can also be made of a ductile heavy metal alloy.
  • the core elements can move in their mutually facing and articulated regions, namely in the intermediate regions 40, 42; 40 ', 42', pivot against each other.
  • the sleeve 36 made of ductile material of sufficient strength, can absorb some of the transverse forces by deformation and ensures the greatest possible adhesion between the adjacent surfaces of the core elements. This ensures that an axial shock component of sufficient size directed against the target remains effective.
  • the predetermined breaking point 38 as numerous investigations have shown, advantageously only becomes effective when the relevant intermediate area gets into a target penetration channel, which results from the effect of the pre-core element 10 and is inclined against the projectile trajectory in the majority of the cases examined.
  • a detachable connection between the shell 36, 36 'and the ballistic hood 44 can be provided, so that the field interchangeability of the pre-core elements 10 and 20 mentioned in the field is possible in all of the exemplary embodiments.

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)
  • Compositions Of Oxide Ceramics (AREA)
  • Inorganic Insulating Materials (AREA)

Claims (5)

1. Projectile perforant sous-calibrés, stabilisé en direction ayant la forme d'un cylindre circulaire de même diamètre sur sa longueur, comportant une ogive balistique (44) et des éléments de noyau antérieur perforants (10, 20) se succédant axialement, suivis immédiatement à l'arrière par un élément de noyau principal (30), et comportant une gaine extérieurement lisse (36), caractérisé en ce que la gaine (36) ne s'étend que sur les éléments de noyau antérieur (10, 20) et une zone antérieure de l'élément de noyau principal (36), auquel elle est reliée par une liaison amovible, le diamètre extérieur de l'élément de noyau principal étant égal, à partir de ce point de raccordement, au diamètre extérieur de la gaine et, dans des zones intermédiaires définies (40, 42, 40', 42'), des extrémités voisines d'éléments de noyau de même diamètre étant adaptées entre elles et étant conformées de façon articulée dans l'une au moins de ces zones intermédiaires (40, 42), et la gaine (36) présentant une zone destinée à la rupture (38) dans l'une au moins de ces zones intermédiaires (40', 42').
2. Projectile selon la revendication 1, caractérisé par un élément d'amortissement absorbant les ondes de choc (54, 56, 58, 60) placé au moins dans l'une des zones intermédiaires (40', 42'), constitué par du métal léger et/ou un alliage métallique leger et/ou de la matière plastique, dont la longueur est inférieure à celle de l'élément de noyau antérieur (10) qui en est voisin.
3. Projectile selon la revendication 1 ou 2, caractérisé en ce que l'ogive balistique (44) est constitué, de préférence, par un alliage métallique léger et comporte vers l'ogive un corps d'acier (46) sensiblement en forme de champignon.
4. Projectile selon l'une des revendications 1 à 3, caractérisé par un rapport de masse des éléments de noyau de 1 : 1,2 : 6, les valeurs numériques correspondant, dans cet ordre, à l'élément de noyau antérieur (10), à l'élément de noyau antérieur (20) et à l'élément de noyau principal (30).
5. Projectile selon l'une des revendications 1 à 4, caractérisé par une liaison amovible entre la gaine (36, 36') et l'ogive balistique (44).
EP83102300A 1982-03-17 1983-03-09 Projectile à noyau perforant pour combattre des armures multicouches Expired EP0088999B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT83102300T ATE27487T1 (de) 1982-03-17 1983-03-09 Panzerbrechende wuchtgeschossanordnung, insbesondere zum bekaempfen von mehrplattenzielen.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3209594A DE3209594A1 (de) 1982-03-17 1982-03-17 Panzerbrechendes wuchtgeschoss insbesondere zum bekaempfen von mehrplattenzielen
DE3209594 1982-03-17

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP87115879.6 Division-Into 1987-10-29

Publications (3)

Publication Number Publication Date
EP0088999A2 EP0088999A2 (fr) 1983-09-21
EP0088999A3 EP0088999A3 (en) 1983-11-23
EP0088999B1 true EP0088999B1 (fr) 1987-05-27

Family

ID=6158425

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83102300A Expired EP0088999B1 (fr) 1982-03-17 1983-03-09 Projectile à noyau perforant pour combattre des armures multicouches

Country Status (4)

Country Link
US (2) US4724769A (fr)
EP (1) EP0088999B1 (fr)
AT (1) ATE27487T1 (fr)
DE (2) DE3209594A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6119600A (en) * 1997-01-14 2000-09-19 Oerlikon Contraves Pyrotec Ag Projectile and method for producing it

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3443195A1 (de) * 1984-11-27 1986-05-28 Diehl GmbH & Co, 8500 Nürnberg Gefechtskopf eines grosskalibrigen geschosses oder einer rakete
US5008071A (en) * 1988-01-04 1991-04-16 Gte Products Corporation Method for producing improved tungsten nickel iron alloys
DE4016051C2 (de) * 1990-05-18 1994-10-06 Rheinmetall Gmbh Mantelpenetrator
DE4023482A1 (de) * 1990-07-24 1992-01-30 Rheinmetall Gmbh Unterkalibriges wuchtgeschoss
US5817969A (en) * 1994-08-26 1998-10-06 Oerlikon Contraves Pyrotec Ag Spin-stabilized projectile with payload
SE508476C2 (sv) 1996-04-26 1998-10-12 Bofors Carl Gustaf Ab Finkaliberprojektil
US6662726B1 (en) * 1999-03-08 2003-12-16 General Dynamics Ordnance And Tactical Systems, Inc. Kinetic energy penetrator
US20050109234A1 (en) * 2001-08-23 2005-05-26 Lloyd Richard M. Kinetic energy rod warhead with lower deployment angles
CA2437515A1 (fr) * 2002-08-21 2004-02-21 Christopher R. Mcmurray Balle de plomb avec sabot
FR2860580B1 (fr) * 2003-10-03 2005-12-16 Giat Ind Sa Munition anti bunker
WO2005099362A2 (fr) 2003-10-14 2005-10-27 Raytheon Company Systeme de contre mesure de mine
US7503261B2 (en) * 2004-01-30 2009-03-17 Oerlikon Cantraves Pyrotec Ag Universal KE projectile, in particular for medium caliber munitions
US20090320711A1 (en) * 2004-11-29 2009-12-31 Lloyd Richard M Munition
USH2230H1 (en) 2006-11-30 2009-08-04 The United States Of America As Represented By The Secretary Of The Navy Ceramic and stacked penetrator against a hardened target
US8707868B2 (en) 2006-11-30 2014-04-29 The United States Of America As Represented By The Secretary Of The Navy Pre-compressed penetrator element for projectile
DE102009050162A1 (de) * 2009-10-21 2011-04-28 TDW Gesellschaft für verteidigungstechnische Wirksysteme mbH Dämpfungsvorrichtung für Einbauteile in Penetratoren
FR2987891B1 (fr) 2012-03-06 2014-09-26 Nexter Munitions Projectile sous calibre a structure de tete amenagee
US20180321021A1 (en) * 2015-11-12 2018-11-08 Randy S. Teig Mechanically adaptable projectile and method of manufacturing the same
US20170138712A1 (en) * 2015-11-12 2017-05-18 Randy S. Teig Mechanically adaptable projectile and method of manufacturing the same
DE102018005406B3 (de) 2018-07-06 2019-09-05 TDW Gesellschaft für verteidigungstechnische Wirksysteme mbH Penetrator
FR3110687B1 (fr) 2020-05-20 2022-05-27 Nexter Munitions Projectile sous calibré et procédé de neutralisation d'un objectif en mettant en oeuvre un tel projectile.
HUP2000306A1 (hu) * 2020-09-17 2022-03-28 Fueloep Nandor Lövedék

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GB594517A (en) * 1940-09-04 1947-11-13 Charles Dennistoun Burney Improvements in or relating to aeroplane and other bombs or projectiles
GB1095992A (en) * 1959-04-14 1967-12-20 Secr Defence Improvements in or relating to projectiles
FR1388760A (fr) * 1962-11-20 1965-02-12 Projectile à noyau dur
US3213792A (en) * 1962-11-20 1965-10-26 Bofors Ab Armor-piercing projectile with hard core
DE1428679C1 (de) * 1964-12-29 1977-09-15 Deutsch Franz Forsch Inst Hartkerngeschoss zur Bekaempfung von Panzerzielen
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
NO137297C (no) * 1976-07-01 1978-02-01 Raufoss Ammunisjonsfabrikker Prosjektil.
DE3011768A1 (de) * 1977-09-29 1986-06-26 Rheinmetall GmbH, 4000 Düsseldorf Wuchtgeschoss mit stapelfoermigem vorpenetrator
DE2743732A1 (de) * 1977-09-29 1986-07-10 Rheinmetall GmbH, 4000 Düsseldorf Wuchtgeschoss
FR2442428A1 (fr) * 1978-11-23 1980-06-20 France Etat Nouveau projectile a energie cinetique
DK60581A (da) * 1980-03-27 1983-06-23 Rheinmetall Gmbh Panserbrydende masseprojektil med stabelformet forpenetrator
DE3209593A1 (de) * 1982-03-17 1983-09-29 Rheinmetall GmbH, 4000 Düsseldorf Unterkalibriges panzerbrechendes wuchtgeschoss (penetrator)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6119600A (en) * 1997-01-14 2000-09-19 Oerlikon Contraves Pyrotec Ag Projectile and method for producing it

Also Published As

Publication number Publication date
US4724769A (en) 1988-02-16
DE3209594C2 (fr) 1990-11-08
DE3371810D1 (en) 1987-07-02
EP0088999A2 (fr) 1983-09-21
ATE27487T1 (de) 1987-06-15
US4920888A (en) 1990-05-01
EP0088999A3 (en) 1983-11-23
DE3209594A1 (de) 1983-09-29

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