EP0137106A1 - Enveloppe pour projectile à sabot - Google Patents

Enveloppe pour projectile à sabot Download PDF

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Publication number
EP0137106A1
EP0137106A1 EP84106549A EP84106549A EP0137106A1 EP 0137106 A1 EP0137106 A1 EP 0137106A1 EP 84106549 A EP84106549 A EP 84106549A EP 84106549 A EP84106549 A EP 84106549A EP 0137106 A1 EP0137106 A1 EP 0137106A1
Authority
EP
European Patent Office
Prior art keywords
cross
locking means
jacket
means according
sectional area
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
EP84106549A
Other languages
German (de)
English (en)
Other versions
EP0137106B1 (fr
Inventor
Peter Wallow
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
Original Assignee
Rheinmetall GmbH
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 filed Critical Rheinmetall GmbH
Publication of EP0137106A1 publication Critical patent/EP0137106A1/fr
Application granted granted Critical
Publication of EP0137106B1 publication Critical patent/EP0137106B1/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
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
    • F42B14/061—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
    • F42B14/061—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile
    • F42B14/062—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile characterised by contact surfaces between projectile and sabot
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49881—Assembling or joining of separate helix [e.g., screw thread]

Definitions

  • the invention relates to positive locking means according to the preamble of claim 1 and a method for arranging the positive locking means.
  • Form-locking means which, in a predeterminable circumferential area of a sub-caliber missile core for connecting a throwable sabot, consist of form-locking means in the form of a thread arranged on the missile core or of grooves, which disadvantageously results in undesirable notch effects in the missile core. can occur and an impairment of the breakthrough performance cannot be excluded.
  • a further form-locking means was proposed on a balancing projectile consisting of a heavy metal core under file number P 30 30 072.2, in which the thread required for transmission is arranged in the outer area of a casing connected to the flight projectile.
  • this jacket which is metallurgically connected to the missile core, consists of light metal, preferably of an aluminum alloy.
  • the invention has for its object to design the positive locking means in such a way that undesirable notch effects on the missile core are avoided and the cross-section in a missile core according to the preamble of claim 1, in order to achieve a high performance level related resilience of the positive locking means is significantly increased.
  • the positive locking means have the decisive advantage that, in addition to a high firing durability, a high penetration rate of the missile core is achieved.
  • the high firing durability is achieved on the one hand by a comparatively high strength of the support sheath, which can be dimensioned relatively small in height, and on the other hand the profiles formed by the overlapping individual cross-sectional areas are highly resilient for positive engagement with the sabot without noteworthy notch effects.
  • the high penetration performance of the missile core is achieved in particular when lateral forces occur in armored targets in that the positive locking means do not cause any notches on the missile core.
  • the carrier jacket consists of a tape wrapped around the missile core, which means that a thin-walled carrier jacket with a large L / D (length / diameter) ratio can be connected to the missile core in a simple manner, in particular by thermoforming and a subsequent shrinking process .
  • This arrangement permits a continuous and individual shrinking process, the winding of a tape wound in each case, which in particular prevents the carrier jacket from being thrown, which is characteristic of long, thin-walled and tight-tolerant bushings during the shrinking process, and produces a carrier jacket with a uniformly high shear strength.
  • a comparatively advantageous long and slender carrier jacket can also be produced from individual partially overlapping rings by hot forming, but preferably in the cold state by extrusion with simultaneous connection to the missile core.
  • the extrusion simultaneously produces a carrier jacket with increased strength properties and the processing effort for the production of the carrier jacket kept low.
  • a partial area of a sub-caliber missile core 5 consisting of heavy metal is shown parallel to the projectile axis 28, on the circumference of which a support jacket 2 is arranged as an intermediate area for the positive locking of a droppable sabot 17.
  • the cross-sectional area 3 of the carrier jacket 2 consists of individual overlapped cross-sectional areas 4 shown in FIGS. 2, 3 and 4, the inner sides 16 of which form a coherent inner surface 18 for a non-positive connection with the jacket surface 19.
  • the cross-sectional areas 4 shown in FIGS. 2, 3 and 4 illustrate either overlapped cross-sectional areas of a wound band 6 (FIG. 5) or of endless rings 7 placed on them (FIG. 9).
  • the cross-sectional area 4 has according to FIGS. 6 to 9 on the end faces 8 and 8 's-shaped profiles 9 for one positive connection of the bands 6 or rings 7.
  • the profiles 9 are arranged on the end faces 8, 8 ' in the overlapped area running parallel to one another on one side, which results in a position of the overlap of adjacent cross sections 4 in such a way that the area of the overlapped area from an inner end face 8 of an adjacent cross-sectional area 4 Face 8 ', the inside 16 of the cross-sectional area 4 formed by the face 8' opposite.
  • the inner end face 8 can be shortened to the outside 10 by an inclined surface 11 or fillet 12. This results in 13 or v-shaped 14 grooves 14, 15 on the outer end face 8 'or with the outer fillet 13 of adjacent cross-sectional areas 4, free of aftertreatment, on the carrier jacket 2, 14 as 15 form-fitting means 1 for the form-fitting connection to the sabot 17 (FIG. 1).
  • the acceleration forces introduced by the sabot 17 (FIG. 1) onto the carrier jacket 2 are transmitted in the direction 21 to the missile core 5 (FIG. 1).
  • the carrier jacket 2 composed of a band 6. 5 is warmly joined according to FIG. 5 with the winding process with centering of the carrier jacket 2 and completion or production of new grooves 20 by rolling or rolling, further processes such as forging or hammering also being possible.
  • the tape 6 is wound obliquely around the rotating missile core 5 in the direction of rotation 22 in the direction of 23, then heated to forging temperature by a heat source 24, for example by a ring burner or a magnetic coil etc., so that it is radially through to the projectile axis 28 in Direction 25 under pressure and in Direction of rotation 26 rotating roller 27 can be formed into a bushing of high radial strength.
  • the cross-sectional area 4 of the band 6 according to FIG. 7 can be designed with a groove 20 prefabricated on the outside 10 or without an outer groove according to FIG. 8.
  • the endless rings 7 shown in FIG. 9 can likewise be formed by their cross-sectional areas 4 pre-shaped on the end faces 8, 8 'with S-shaped profiles 9 to form a support jacket 2 (which can be varied in length and parallel to the projectile axis 28 (FIG. 1)). Fig. 1).
  • forging or rolling processes or, in the case of completely prefabricated form-locking means (FIGS. 2, 3 and 4) extrusion may be considered as the joining process.
  • the surface of the profiles 9 of the carrier jacket 2 (FIG. 1) is solidified in such a way that a high-strength connection is created between it and the missile core 5 (FIG. 1) due to internal stresses.
  • the binding of the carrier jacket 2 (Fig. 1) to the missile core 5 (Fig. 1) can, but also in all other manufacturing processes, be reinforced by an acceptable surface roughness or by fine toothing or wave formation between the carrier jacket 2 and missile core 5 without breaking points .
  • the missile core 5 can either be equipped with an outer ballistic hood (not shown) in order to avoid external ballistic influences of the carrier shell 2 or it can be provided in the front area of the missile core 5 (also not shown) with a front part enlarged notch-free to the diameter of the outside 10 of the thin-walled carrier shell 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Package Frames And Binding Bands (AREA)
EP84106549A 1983-07-20 1984-06-07 Enveloppe pour projectile à sabot Expired EP0137106B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3326131 1983-07-20
DE19833326131 DE3326131A1 (de) 1983-07-20 1983-07-20 Formschlussmittel und verfahren zum anordnen derselben im umfangbereich eines unterkalibrigen fluggeschosskernes aus schwermetall

Publications (2)

Publication Number Publication Date
EP0137106A1 true EP0137106A1 (fr) 1985-04-17
EP0137106B1 EP0137106B1 (fr) 1987-03-04

Family

ID=6204442

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84106549A Expired EP0137106B1 (fr) 1983-07-20 1984-06-07 Enveloppe pour projectile à sabot

Country Status (3)

Country Link
US (1) US4603636A (fr)
EP (1) EP0137106B1 (fr)
DE (2) DE3326131A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0253058A1 (fr) * 1986-07-15 1988-01-20 Rheinmetall GmbH Projectile à calibre réduit
EP0331579A1 (fr) * 1988-03-03 1989-09-06 GIAT Industries Dispositif de liaison par concordance de forme entre un pénétrateur de type flèche et un sabot
FR2660993A1 (fr) * 1990-04-14 1991-10-18 Rheinmetall Gmbh Projectile sous-calibre comprenant un sabot de poussee.

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3723909C2 (de) * 1987-07-18 1994-12-08 Rheinmetall Gmbh Penetrator
US5789699A (en) * 1996-12-16 1998-08-04 Primex Technologies, Inc. Composite ply architecture for sabots
US6186094B1 (en) * 1998-08-26 2001-02-13 Alliant Techsystems Inc. Sabot anti-splitting ring
US7958829B1 (en) 2006-11-08 2011-06-14 The United States Of America As Represented By The Secretary Of The Army Sabot

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR495501A (fr) * 1917-09-14 1919-10-10 Denson Hermonn Armstrong Perfectionnements apportés aux projectiles
US2996011A (en) * 1944-06-30 1961-08-15 Henry F Dunlap Projectile
US3262391A (en) * 1964-10-12 1966-07-26 Budd Co Subcaliber projectile and sabot
US3745926A (en) * 1971-06-21 1973-07-17 Us Army Sabot spin-stabilized projectile
US3859922A (en) * 1973-06-28 1975-01-14 Us Army Two piece ammunition round
US4187783A (en) * 1978-03-13 1980-02-12 The United States Of America As Represented By The Secretary Of The Army Discarding sabot munition
FR2523715A1 (fr) * 1980-08-09 1983-09-23 Rheinmetall Gmbh Agent de liaison par concordance de forme, materiau pour le constituer, et procede pour disposer l'agent de liaison par concordance de forme sur la zone peripherique d'un projectile volant constitue en un alliage fritte a metal lourd
DE3104745A1 (de) * 1980-06-26 1984-04-19 Rheinmetall GmbH, 4000 Düsseldorf Geschoss

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4360954A (en) * 1981-02-17 1982-11-30 The United States Of America As Represented By The Secretary Of The Army Method of making cast-in-place sabots
US4469027A (en) * 1983-04-15 1984-09-04 The United States Of America As Represented By The Secretary Of The Army Armor piercing ammunition having interlocking means

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR495501A (fr) * 1917-09-14 1919-10-10 Denson Hermonn Armstrong Perfectionnements apportés aux projectiles
US2996011A (en) * 1944-06-30 1961-08-15 Henry F Dunlap Projectile
US3262391A (en) * 1964-10-12 1966-07-26 Budd Co Subcaliber projectile and sabot
US3745926A (en) * 1971-06-21 1973-07-17 Us Army Sabot spin-stabilized projectile
US3859922A (en) * 1973-06-28 1975-01-14 Us Army Two piece ammunition round
US4187783A (en) * 1978-03-13 1980-02-12 The United States Of America As Represented By The Secretary Of The Army Discarding sabot munition
DE3104745A1 (de) * 1980-06-26 1984-04-19 Rheinmetall GmbH, 4000 Düsseldorf Geschoss
FR2523715A1 (fr) * 1980-08-09 1983-09-23 Rheinmetall Gmbh Agent de liaison par concordance de forme, materiau pour le constituer, et procede pour disposer l'agent de liaison par concordance de forme sur la zone peripherique d'un projectile volant constitue en un alliage fritte a metal lourd

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0253058A1 (fr) * 1986-07-15 1988-01-20 Rheinmetall GmbH Projectile à calibre réduit
EP0331579A1 (fr) * 1988-03-03 1989-09-06 GIAT Industries Dispositif de liaison par concordance de forme entre un pénétrateur de type flèche et un sabot
FR2628196A1 (fr) * 1988-03-03 1989-09-08 France Etat Armement Dispositif de liaison par concordance de forme entre un penetrateur de type fleche et un sabot
FR2660993A1 (fr) * 1990-04-14 1991-10-18 Rheinmetall Gmbh Projectile sous-calibre comprenant un sabot de poussee.

Also Published As

Publication number Publication date
US4603636A (en) 1986-08-05
DE3462553D1 (en) 1987-04-09
EP0137106B1 (fr) 1987-03-04
DE3326131A1 (de) 1985-01-31

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