EP0295362B1 - Fin-stabilised subcalibre projectile - Google Patents

Fin-stabilised subcalibre projectile Download PDF

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Publication number
EP0295362B1
EP0295362B1 EP88102343A EP88102343A EP0295362B1 EP 0295362 B1 EP0295362 B1 EP 0295362B1 EP 88102343 A EP88102343 A EP 88102343A EP 88102343 A EP88102343 A EP 88102343A EP 0295362 B1 EP0295362 B1 EP 0295362B1
Authority
EP
European Patent Office
Prior art keywords
projectile
fins
tail unit
accordance
projectile body
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 - Lifetime
Application number
EP88102343A
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German (de)
French (fr)
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EP0295362A1 (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-A 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 approximately 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)

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-A 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-A 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 approximately 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, certainly avoids 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 (3)

1. Sub-calibre fin-stabilised projectile having a high length-to-diameter ratio body and a tail unit soldered onto the rear zone of the body (25) of the projectile, the tail unit comprising a number of fins (20), with elongate securing surfaces (21) of the fins (20) being axially parallel with the body (25) of the projectile, characterised by the following features:
(a) the body (25) of the projectile is smooth and unnotched over the peripheral surface of the rear zone where the tail unit is secured and has the same external diameter as the central zone of the projectile body,
(b) the fins (20) comprise simple stamped parts with a wall thickness greater than 0.35 mm and in accordance with the diameter of the projectile body, the securing surfaces (21) of the fins being secured by the soldered connection to the smooth unnotched peripheral surface of the projectile body (25).
2. Projectile in accordance with Claim 1, characterised by the fact that the projectile body (25) comprises a heavy metal material, preferably a pure tungsten sintered material, and the fins (20) of the tail unit are a high-temperature resisting steel.
3. Projectile in accordance with Claim 1 or 2, characterised by the fact that the solder material used comprises mainly 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
DE19873719768 DE3719768A1 (en) 1987-06-13 1987-06-13 SUB-CALIBRATE WING-STABILIZED SHELL
DE3719768 1987-06-13

Publications (2)

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

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ID=6329628

Family Applications (1)

Application Number Title Priority Date Filing Date
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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1949019B1 (en) 2005-11-15 2015-04-22 BAE Systems Bofors AB Method of increasing the range of a subcalibre shell and subcalibre shells with a long range

Families Citing this family (2)

* 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

Family Cites Families (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
NL7908989A (en) * 1979-12-13 1981-07-16 Eurometaal Nv METHOD FOR MANUFACTURING A PROJECTILE WITH A TUBULAR BODY
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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1949019B1 (en) 2005-11-15 2015-04-22 BAE Systems Bofors AB Method of increasing the range of a subcalibre shell and subcalibre shells with a long range

Also Published As

Publication number Publication date
DE3719768A1 (en) 1988-12-22
DE3862243D1 (en) 1991-05-08
EP0295362A1 (en) 1988-12-21

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