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EP0295362A1 - Fin-stabilised subcalibre projectile - Google Patents

Fin-stabilised subcalibre projectile Download PDF

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Publication number
EP0295362A1
EP0295362A1 EP88102343A EP88102343A EP0295362A1 EP 0295362 A1 EP0295362 A1 EP 0295362A1 EP 88102343 A EP88102343 A EP 88102343A EP 88102343 A EP88102343 A EP 88102343A EP 0295362 A1 EP0295362 A1 EP 0295362A1
Authority
EP
European Patent Office
Prior art keywords
projectile
projectile body
penetrator
tail unit
wings
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
EP88102343A
Other languages
German (de)
French (fr)
Other versions
EP0295362B1 (en
Inventor
Frank Achilles
Bernhard Bisping
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 EP0295362A1 publication Critical patent/EP0295362A1/en
Application granted granted Critical
Publication of EP0295362B1 publication Critical patent/EP0295362B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins

Definitions

  • the invention relates to a sub-caliber wing-stabilized projectile according to the preamble of claim 1.
  • Such a projectile is known for example from DE-OS 30 38 087.
  • the wings are inserted in longitudinal slots or grooves in the rear area of the projectile body and fastened by soldering or gluing.
  • the wings of the tail unit are connected in one piece to a tubular sleeve which is pushed onto the projectile body and soldered or glued on.
  • this can be somewhat reduced in diameter in the fastening area of the tail unit in accordance with the sleeve thickness.
  • the soldering of the individual wings via double-sided solder connections gives the projectile sufficient firing strength without individual wings loosening or penetrator breaks in the rear area of the projectile body when the projectile is launched.
  • the advantageous behavior of the penetrator in the target results from the fact that the impact of the projectile on the first armor plate e.g. a modern multi-plate armor of armored vehicles, the solder connection between the tail wings and the body of the projectile bursts, so that the penetration process of the non-notched projectile body can take place without hindrance and this is not additionally slowed down by shearing off the empennage wings on the first armor plate.
  • the reference numeral 25 denotes a projectile body of a sub-caliber wing-stabilized balancing projectile or penetrator of high length / diameter ratio (approximately in the order of magnitude of 10 to 18), which has an empennage consisting of a plurality of wings 20 arranged in the rear area.
  • each individual wing 20 with a narrow, long end face 21 is butt-soldered onto the smooth, un-notched peripheral face 22 of the projectile body 25 by way of solder connections 27 on both sides.
  • Fig. 2 shows this arrangement in side view.
  • the projectile body 25 is preferably made of pure tungsten sintered material, while the wings are manufactured as simple and inexpensive stampings made of high-temperature steel or a high-strength aluminum alloy with a high-temperature-resistant coating (hard coat).
  • the wall thickness of the sash can be reduced to only 0.35 mm by 10 mm and soldered to the projectile body with sufficient strength. Usual wall thicknesses are about 0.5 to 1 mm for small penetrators.
  • soldering on the wings there are also no adverse effects of temperature on the penetrator material by soldering on the wings, since the soldering process takes place in a protective gas atmosphere for example NH3 or argon (Ar), preferably with a solder material consisting essentially of copper with additions of the elements silver (Ag), iron (Fe) or zinc (Zn).
  • a protective gas atmosphere for example NH3 or argon (Ar)
  • solder material consisting essentially of copper with additions of the elements silver (Ag), iron (Fe) or zinc (Zn).
  • soldering temperatures are, for example, 750 ° C. for a special solder A made of Cu, Ag and Zn, or, for example, 1140 ° C. for a special solder B made of Cu and Fe.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

The invention relates to a fin-stabilised sub-calibre projectile of high length/diameter ratio, with a tail unit arranged in the rear region of the projectile body and consisting of a plurality of fins. Conventionally, the fins are inserted into recesses or longitudinal slots in the rear region of the penetrator or are connected firmly to the penetrator by means of separate tail-unit sleeves which are pushed on from the rear as far as a shoulder in the fastening region of the projectile body. However, constructive measures of this kind cause cross-sectional weakening where stress peaks occurring as the result of a notch effect during target impact can trigger a break of the penetrator in the fastening region of the tail unit. This danger of breakage of the penetrator is prevented by the invention, in that, by the use of a special solder, each individual fin (20) is butt-soldered by means of a narrow long end face (21) onto the smooth unnotched circumferential surface (22) of the projectile body (25). <IMAGE>

Description

Die Erfindung bezieht sich auf ein unterkalibriges flügelstabilisiertes Geschoß gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a sub-caliber wing-stabilized projectile according to the preamble of claim 1.

Ein derartiges Geschoß ist beispielsweise aus der DE-OS 30 38 087 bekannt. Hierbei werden die Flügel in Längsschlitze oder Nuten im hinteren Bereich des Geschoßkörpers eingesetzt und durch Löten oder Kleben befestigt. In einer anderen Ausgestaltungsform sind die Flügel des Leitwerkes mit einer rohrförmigen Hülse einstückig verbunden, die auf den Geschoßkörper aufge­schoben und angelötet oder angeklebt wird. Zum Anpas­sen des Außendurchmessers der Leitwerks-Trägerhülse an den Außendurchmesser des Geschoßkörpers kann dieser im Befestigungsbereich des Leitwerkes im Durchmesser entsprechend der Hülsenstärke etwas verringert sein.Such a projectile is known for example from DE-OS 30 38 087. The wings are inserted in longitudinal slots or grooves in the rear area of the projectile body and fastened by soldering or gluing. In another embodiment, the wings of the tail unit are connected in one piece to a tubular sleeve which is pushed onto the projectile body and soldered or glued on. To adapt the outer diameter of the tail unit support sleeve to the outer diameter of the projectile body, this can be somewhat reduced in diameter in the fastening area of the tail unit in accordance with the sleeve thickness.

Derartige konstruktive Maßnahmen ergeben im Heckbereich des langgestreckten Geschoßkörpers zum einen einen nicht zielwirksamen Materialverlust und insbesondere nachteilige Kerbwirkungen, an denen bei Zielaufprall des Geschoßkörpers durch Konzentrierung der Stoßwellen in den geschwächten Bereichen Spannungsspitzen auftreten, die zum Bruch des Geschoßkörpers im Leitwerksbereich führen können.Such constructive measures result in the rear region of the elongated projectile body, on the one hand, a non-effective loss of material and in particular disadvantageous notch effects, in which stress impacts occur when the projectile body hits the target due to concentration of the shock waves in the weakened areas, which can lead to breakage of the projectile body in the tail area.

Es ist Aufgabe der vorliegenden Erfindung, ein gat­tungsgleiches Geschoß anzugeben, bei dem unter ein­facher Leitwerksausbildung die Gefahr von Penetrator­brüchen im Befestigungsbereich des Leitwerkes vermieden werden, so daß der gesamte Geschoßkörper eine hohe Durchschlagsleistung beim Auftreffen auf ein Panzerplat­tenziel erreicht.It is an object of the present invention to provide a bullet of the same type, in which the risk of penetrator breaks in the fastening area of the tail unit is avoided with simple tail assembly training, so that the entire projectile body achieves a high level of penetration when striking an armored plate target.

Diese Aufgabe wird mit den im Kennzeichnungsteil des Anspruches 1 angegebenen Merkmalen gelöst.This object is achieved with the features specified in the characterizing part of claim 1.

Das Anlöten der einzelnen Flügel über beidseitige Löt­verbindungen verleiht dem Geschoß die ausreichende Ab­schußfestigkeit, ohne daß sich etwa einzelne Flügel lösen oder bereits bei Abschuß Penetratorbrüche im Heck­bereich des Geschoßkörpers ergeben. Das vorteilhafte Verhalten des Penetrators im Ziel ergibt sich dadurch, daß durch den Auftreffstoß des Geschosses auf die erste Panzerplatte z.B. einer modernen Mehrplattenpanzerung von gepanzerten Fahrzeugen, die Lötverbindung zwischen Leitwerksflügeln und Geschoßkörper aufplatzt, so daß der Durchdringungsvorgang des ungekerbten Geschoßkörpers ungehindert erfolgen kann und dieser nicht zusätzlich durch ein Abscheren der Leitwerksflügel an der ersten Panzerplatte abgebremst wird.The soldering of the individual wings via double-sided solder connections gives the projectile sufficient firing strength without individual wings loosening or penetrator breaks in the rear area of the projectile body when the projectile is launched. The advantageous behavior of the penetrator in the target results from the fact that the impact of the projectile on the first armor plate e.g. a modern multi-plate armor of armored vehicles, the solder connection between the tail wings and the body of the projectile bursts, so that the penetration process of the non-notched projectile body can take place without hindrance and this is not additionally slowed down by shearing off the empennage wings on the first armor plate.

Weitere Merkmale der Erfindung und dazugehörige Vortei­le sind den Unteransprüchen und der nachfolgenden Be­schreibung zu entnehmen.Further features of the invention and associated advantages can be found in the subclaims and the description below.

Die Erfindung wird nachfolgend anhand eines in den Zeichnungen dargestellten Ausführungsbeispieles näher erläutert.The invention is explained in more detail below with reference to an embodiment shown in the drawings.

Es zeigen:

  • Fig. 1 einen Querschnitt durch einen Geschoß­körper gemäß der Erfindung im Befe­stigungsbereich des Leitwerkes und
  • Fig. 2 den Befestigungsbereich des Leitwerkes auf dem Geschoßkörper in Seitenansicht.
Show it:
  • Fig. 1 shows a cross section through a projectile body according to the invention in the fastening area of the tail unit and
  • Fig. 2 shows the attachment area of the tail unit on the projectile body in a side view.

In Fig. 1 ist mit der Bezugsziffer 25 ein Geschoßkörper eines unterkalibrigen flügelstabilisierten Wuchtgeschos­ses bzw. Penetrators von hohem Länge/Durchmesser-Ver­hältnis (etwa in der Größenordnung von 10 bis 18) be­zeichnet, der ein im Heckbereich angeordnetes aus meh­reren Flügeln 20 bestehendes Leitwerk aufweist. Hierbei ist erfindungsgemäß jeder einzelne Flügel 20 mit einer schmalen langen Stirnfläche 21 über beidseitige Lötver­bindungen 27 stumpf auf die glatte ungekerbte Umfangs­fläche 22 des Geschoßkörpers 25 aufgelötet. Fig. 2 zeigt diese Anordnung in Seitenansicht.In Fig. 1, the reference numeral 25 denotes a projectile body of a sub-caliber wing-stabilized balancing projectile or penetrator of high length / diameter ratio (approximately in the order of magnitude of 10 to 18), which has an empennage consisting of a plurality of wings 20 arranged in the rear area. In this case, according to the invention, each individual wing 20 with a narrow, long end face 21 is butt-soldered onto the smooth, un-notched peripheral face 22 of the projectile body 25 by way of solder connections 27 on both sides. Fig. 2 shows this arrangement in side view.

Der Geschoßkörper 25 besteht vorzugsweise aus reinem Wolfram-Sinterwerkstoff, während die Flügel als einfache und kostengünstig herzustellende Stanzteile aus hochwarm­festem Stahl oder einer hochfesten Aluminiumlegierung mit einem hochtemperaturbeständigen Überzug (Hardcoat) hergestellt sind.The projectile body 25 is preferably made of pure tungsten sintered material, while the wings are manufactured as simple and inexpensive stampings made of high-temperature steel or a high-strength aluminum alloy with a high-temperature-resistant coating (hard coat).

Zur Verringerung von Totlastanteilen wie auch bei Pene­tratoren mit kleinen Geschoßkörperdurchmessern von z.B. nur 10 mm kann die Wandstärke der Flügel bis auf 0,35 mm herabgesetzt und noch mit ausreichender Fe­stigkeit auf dem Geschoßkörper verlötet werden. Übliche Wandstärken betragen etwa 0,5 bis 1 mm bei kleinen Pene­tratoren. Dadurch, daß der Geschoßkörper im heckseitigen Befestigungsbereich des Leitwerkes den gleichen Außen­durchmesser aufweist, wie etwa in seinem mittigen Ge­schoßkörperbereich, wird mit Sicherheit vermieden, daß heckseitige Stücke des Penetrators beim Auftreffen auf die erste Panzerplatte abbrechen und für das weitere Eindringen des Geschoßkörpers unwirksam werden, da keine schädlichen Kerbwirkungen bzw. Spannungsspitzen durch konstruktive Maßnahmen wie Querschnittsbeeinträchtigun­gen gegeben sind.To reduce dead load as well as penetrators with small projectile diameters of e.g. The wall thickness of the sash can be reduced to only 0.35 mm by 10 mm and soldered to the projectile body with sufficient strength. Usual wall thicknesses are about 0.5 to 1 mm for small penetrators. The fact that the projectile body in the rear-side fastening area of the tail unit has the same outer diameter as, for example, in its central area of the projectile body, is reliably avoided that rear-side pieces of the penetrator break off when they strike the first armored plate and become ineffective for further penetration of the projectile body, since there are no harmful notch effects or stress peaks due to design measures such as cross-sectional impairments.

Auch sind nachteilige Temperatureinwirkungen auf den Pe­netratorwerkstoff durch das Anlöten der Flügel nicht gegeben, da der Lötvorgang unter Schutzgasatmosphäre z.B. NH₃ oder Argon (Ar), vorzugsweise mit einem Lotmaterial, das im wesentlichen aus Kupfer mit Zu­sätzen der Elemente Silber (Ag), Eisen (Fe) oder Zink (Zn) besteht, erfolgt.There are also no adverse effects of temperature on the penetrator material by soldering on the wings, since the soldering process takes place in a protective gas atmosphere for example NH₃ or argon (Ar), preferably with a solder material consisting essentially of copper with additions of the elements silver (Ag), iron (Fe) or zinc (Zn).

Die Löttemperaturen betragen beispielsweise 750 ° C für ein Speziallot A aus Cu, Ag und Zn, oder beispielsweise 1140° C für ein Speziallot B aus Cu und Fe.The soldering temperatures are, for example, 750 ° C. for a special solder A made of Cu, Ag and Zn, or, for example, 1140 ° C. for a special solder B made of Cu and Fe.

Claims (5)

1. Unterkalibriges flügelstabilisiertes Geschoß von hohem Länge/Durchmesser-Verhältnis mit einem im Heckbereich des Geschosskörpers angeordneten aus mehreren Flügeln bestehenden Leitwerk, dadurch gekennzeichnet, daß jeder einzelne Flügel (20) mit einer schmalen lan­gen Stirnfläche (21) stumpf auf die glatte ungekerb­te Umfangsfläche (22) des Geschoßkörpers (25) aufge­lötet ist.1. Sub-caliber wing-stabilized projectile of high length / diameter ratio with a tail unit arranged in the rear region of the projectile body, consisting of several wings, characterized in that each individual wing (20) with a narrow, long end face (21) bluntly onto the smooth, notched peripheral surface ( 22) of the projectile body (25) is soldered on. 2. Geschoß nach Anspruch 1, dadurch ge­kennzeichnet, daß der Geschoßkörper (25) aus einem Schwermetall-Werkstoff, vorzugsweise einem reinen Wolfram-Sinterwerkstoff, und die Flügel (20) des Leitwerkes aus hochwarmfestem Stahl bestehen.2. Projectile according to claim 1, characterized in that the projectile body (25) consists of a heavy metal material, preferably a pure sintered tungsten material, and the wings (20) of the tail unit consist of high-temperature steel. 3. Geschoß nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Flügel (20) aus einfachen Stanzteilen mit einer dem Geschoßkörper durchmesser entsprechend angepaßten Wandstärke größer 0,35 mm bestehen.3. Projectile according to claim 1 or 2, characterized in that the wings (20) made of simple stamped parts with a projectile body diameter corresponding to adapted wall thickness greater than 0.35 mm. 4. Geschoß nach Anspruch 1, 2 oder 3, dadurch gekennzeichnet, daß der Geschoß­körper (25) im heckseitigen Befestigungsbereich des Leitwerkes den gleichen Außendurchmesser wie in seinem mittigen Geschoßkörperbereich aufweist.4. Projectile according to claim 1, 2 or 3, characterized in that the projectile body (25) in the rear fastening area of the tail unit has the same outer diameter as in its central projectile body region. 5. Geschoß nach Anspruch 1, 2, 3 oder 4, dadurch gekennzeichnet, daß das verwendete Lotmaterial im wesentlichen aus Kup­fer mit Zusätzen der Elemente Ag, Fe oder Zn besteht.5. Projectile according to claim 1, 2, 3 or 4, characterized in that the solder material used consists essentially of copper with additions of the elements Ag, Fe or Zn.
EP88102343A 1987-06-13 1988-02-18 Fin-stabilised subcalibre projectile Expired - Lifetime EP0295362B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3719768 1987-06-13
DE19873719768 DE3719768A1 (en) 1987-06-13 1987-06-13 SUB-CALIBRATE WING-STABILIZED SHELL

Publications (2)

Publication Number Publication Date
EP0295362A1 true EP0295362A1 (en) 1988-12-21
EP0295362B1 EP0295362B1 (en) 1991-04-03

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Family Applications (1)

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EP88102343A Expired - Lifetime EP0295362B1 (en) 1987-06-13 1988-02-18 Fin-stabilised subcalibre projectile

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EP (1) EP0295362B1 (en)
DE (2) DE3719768A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3927798A1 (en) * 1989-08-23 1991-03-14 Rheinmetall Gmbh Stable missile tail unit - consists of aluminium or steel with low resistance or relatively high wt.
DE3940969C2 (en) * 1989-12-12 1995-01-05 Rheinmetall Gmbh Sub-caliber balancing projectile
SE0502509L (en) 2005-11-15 2007-01-09 Bae Systems Bofors Ab Under-calibrated grenade with long range

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE221407C (en) *
GB191512985A (en) * 1915-09-10 1916-06-22 Charles Bingham Improvement in Explosive Projectiles.
US3805355A (en) * 1972-12-15 1974-04-23 M Gornik Fixture for model rocket
EP0032260A1 (en) * 1979-12-13 1981-07-22 Eurometaal N.V. Method of manufacturing a projectile body, as well as projectile body produced in that manner
DE3038087A1 (en) * 1980-10-09 1982-05-27 Rheinmetall GmbH, 4000 Düsseldorf ARROW-STABILIZED RIFLE BULLET (PENETRATOR)
EP0174082A1 (en) * 1984-07-23 1986-03-12 Judd Engineering Limited Projectile stabilising fin unit

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE221407C (en) *
GB191512985A (en) * 1915-09-10 1916-06-22 Charles Bingham Improvement in Explosive Projectiles.
US3805355A (en) * 1972-12-15 1974-04-23 M Gornik Fixture for model rocket
EP0032260A1 (en) * 1979-12-13 1981-07-22 Eurometaal N.V. Method of manufacturing a projectile body, as well as projectile body produced in that manner
DE3038087A1 (en) * 1980-10-09 1982-05-27 Rheinmetall GmbH, 4000 Düsseldorf ARROW-STABILIZED RIFLE BULLET (PENETRATOR)
EP0174082A1 (en) * 1984-07-23 1986-03-12 Judd Engineering Limited Projectile stabilising fin unit

Also Published As

Publication number Publication date
EP0295362B1 (en) 1991-04-03
DE3719768A1 (en) 1988-12-22
DE3862243D1 (en) 1991-05-08

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