EP0080210B1 - Tracer projectile, preferably for machine guns, with range reducing device - Google Patents

Tracer projectile, preferably for machine guns, with range reducing device Download PDF

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Publication number
EP0080210B1
EP0080210B1 EP82110864A EP82110864A EP0080210B1 EP 0080210 B1 EP0080210 B1 EP 0080210B1 EP 82110864 A EP82110864 A EP 82110864A EP 82110864 A EP82110864 A EP 82110864A EP 0080210 B1 EP0080210 B1 EP 0080210B1
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EP
European Patent Office
Prior art keywords
projectile
stabilizing element
accordance
fact
tracer
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
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EP82110864A
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German (de)
French (fr)
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EP0080210A3 (en
EP0080210A2 (en
Inventor
Karl Wilhelm Dipl.-Ing. Bethmann
Ulrich Dr.-Ing. Dipl.-Phys. Theis
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Rheinmetall Industrie AG
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Rheinmetall GmbH
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Priority to AT82110864T priority Critical patent/ATE35051T1/en
Publication of EP0080210A2 publication Critical patent/EP0080210A2/en
Publication of EP0080210A3 publication Critical patent/EP0080210A3/en
Application granted granted Critical
Publication of EP0080210B1 publication Critical patent/EP0080210B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B8/00—Practice or training ammunition
    • F42B8/12—Projectiles or missiles
    • F42B8/14—Projectiles or missiles disintegrating in flight or upon impact

Definitions

  • the invention relates to a sub-caliber projectile according to the preamble of claim 1.
  • a generic object preferably for exercise purposes, is known from GB-A-2 010 452. It consists of a projectile body with a front, a middle and a rear part carrying a stabilizing tail. Two connection areas are defined by axially aligned pins and bores. Each connecting area has a sleeve-shaped connecting means in the circumferential surface, the material of which loses its strength and thus its connecting property under heat transfer - here due to friction of the air flowing past. By releasing the relevant parts, the projectile in question disintegrates, the parts falling to the ground on a respective unstable trajectory.
  • This projectile is complex to manufacture. This is particularly evident in the case of a projectile with a length / diameter ratio which is customary for swirl stabilization.
  • an influence of different atmospheric conditions on the behavior of the connecting means is probable and therefore it cannot be ruled out that the length of the stable trajectory is subject to fluctuations. These are likely to be particularly disruptive when switching to smaller calibers, as are common with machine guns.
  • the invention has for its object to provide a bullet of the same type, which is characterized by less expensive production and significantly reduced interference from the atmospheric conditions and is suitable for machine guns.
  • a rear part 11 of a projectile body 10 of a spin-stabilized projectile according to FIG. 1 with a peripheral surface 12 and a rear surface 14 has a rear bore 16 with a peripheral surface 18 and a front end surface 20.
  • a funnel-shaped centering bore 22 is arranged in the projectile body 10 in the region of a central longitudinal axis A.
  • An essentially circular cylindrical stabilizing body 24 has a rear circumferential surface 26 and a concave rear surface 28.
  • a radial step 30 is provided between a front twist 32 and the rear circumferential surface 26.
  • a front end face 34 of the stabilizing body 24 has a centering projection 40 with a central bore 42. The centering projection 40 adapts to the centering bore 22.
  • the stabilizing body 24 has a jacket 36, which extends longitudinally axially between the shoulder 30 and the end face 34, with three centering ribs 38 projecting radially outward against the peripheral surface 18.
  • a respective space between a circumferential surface 39 and the rear circumferential surface 26 of the jacket 38 and the circumferential surface 18 of the bore 16 and the two end faces 20 and 24 on the word side serves as an annular disk 54 and a circular cylindrical hollow body 52 of a tracer set 50.
  • the projection 40 encircles an annular disk 56 of a substance still to be discussed, which is in close contact with a cylindrical surface 55 of the annular disk 54.
  • the circular-cylindrical hollow body 52 is interrupted in the area in question by the centering ribs 38.
  • the rear end of the tracer set 50 is formed by a part 51 which fills a space between the rear surface 28 and an edge of the bore 16 lying in the rear surface 14.
  • a wire 48 is accommodated in a helical shape, which is fastened at a point 44 on the projectile body 10 and with a rear end at a point 46 on the stabilizing body 24.
  • a projectile body 60 of a wing-stabilized sub-caliber projectile has a rear part 62 with a circumferential surface 61 and with a central axial support extension 64 of comparatively small diameter.
  • An unscrewing surface 64 connects the circumferential surface 61 to an external thread 70 of the carrier extension 64 via a relief radius 68.
  • the latter surrounds a double-walled bush 72 of circular-cylindrical cross-section in a form-fitting manner.
  • a front wall 74 connects an inner wall 78 to an outer wall 80, an outer front surface 76 of the front wall 74 of the boring surface 64 nestling.
  • the peripheral surface 80 of the sleeve 72 is in a manner not shown with a Connected thin-walled sleeve 86 which forms a stabilizing tail 87 with stabilizing wings 88 attached to it.
  • a cavity 84 between the facing surface of the inner 78 and the outer wall 80 of the sleeve 72 serves as a receptacle 92, which extends from the front wall 74 to a rear surface 90,
  • the tracer set 50 is ignited in the region of the rear surface 14 in a manner not to be discussed in detail. With part 51, part 52 surrounding stabilizing body 24 also burns. As soon as the burn-up of the tracer set 50 has progressed to shoulder 30, the heating of the casing 36 begins with its centering ribs 38.
  • the casing 36 consists of a material whose strength changes drastically due to the action of the heat released when the tracer set 50 is burned up. If the jacket 36 consists of a corresponding magnesium alloy, it loses its strength due to chemical reaction, i. H. preferably by violent oxidation, which corresponds to consumption by burning.
  • the stabilizing body 24 it advantageously consists, like the projectile body 10, of improving the penetration performance from a high-density material, for example a sintered alloy with a high proportion of tungsten or depleted uranium, increasingly losing its definition in the bore.
  • a suction present in the direction of arrow 59 against the direction of flight 58 of the projectile acts on the concave rear surface 28 of the stabilizing body 24.
  • a larger amount of gas is released therefrom, the majority of which on the Presses the end face 20 of the projectile body 10 and the end face 34 of the stabilizing body 24 and axially shifts the latter in the direction of arrow 59.
  • the tracer 92 is ignited in the area of the rear surface 90 in a firing manner.
  • the large amount of heat released during the burning at high temperature is transferred to the inner 78 as well as the outer wall 80 of the sleeve 72. While extensive dissipation of the heat to the surroundings is possible via the outer wall 80, the sleeve 86 and the stabilizing wings 88, a strong build-up of heat occurs in the area of the inner wall 78. As a result, the material of the inner wall 78 is softened. As soon as the burn-up of the tracer 92 has progressed far enough, the form fit between the sleeve 72 and the carrier extension 64 is lost.
  • the stabilizing tail 87 separates from the projectile body 60 in the direction of an arrow 96 opposite to the direction of flight 94 and causes it to become immediately unstable, so that it leaves its original trajectory and falls down.
  • the description given in connection with the projectile according to FIGS. 1a and 2 applies analogously to the temporal adjustability of the destabilization.
  • the stabilizing wings usually have a low pitch for generating a slight compensating rotation, this additionally favors the separation from the projectile according to the invention.
  • a fragmentation charge is to be initiated via a tracer set after a predetermined time.
  • the fragmentation charge requires a central axial bore to accommodate it. This hole reduces the penetration rate of the projectile on armored targets. To ensure sufficient effectiveness, the fragmentation charge must have a certain minimum size. This affects the density of the projectile.

Abstract

In ammunition, preferably for machine cannons, including a subcaliber stabilized projectile equipped with a body of tracer material and a stabilizing element, the heat released during combustion of the tracer material is utilized to drastically change the strength of the material of an element used to fasten the stabilizing element to the projectile. By being able to set the time of combustion and of the change in the material, the stabilizing element changes its position with respect to the projectile. The system or ammunition in question becomes unstable and drops to the ground.

Description

Die Erfindung betrifft ein unterkalibriges Geschoß nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a sub-caliber projectile according to the preamble of claim 1.

Ein gattungsgleicher Gegenstand, vorzugsweise für Übungszwecke, ist bekannt aus der GB-A-2 010 452. Er besteht aus einem Geschoßkörper mit einem vorderen, einem mittleren und einem ein Stabilisierungsleitwerk tragenden hinteren Teil. Durch achsfluchtende Zapfen und Bohrungen sind zwei Verbindungsbereichte definiert. Jeder Verbindungsbereich weist in der Umfangsfläche ein hülsenförmiges Verbindungsmittel auf, dessen Werkstoff unter Wärmeübergang - hier durch Reibung der vorbeiströmenden Luft - seine Festigkeit und damit seine verbindende Eigenschaft verliert. Durch Lösen der betreffenden Teile zerfällt das betreffende Geschoß, wobei die Teile auf einer jeweiligen instabilen Flugbahn zu Boden fallen.A generic object, preferably for exercise purposes, is known from GB-A-2 010 452. It consists of a projectile body with a front, a middle and a rear part carrying a stabilizing tail. Two connection areas are defined by axially aligned pins and bores. Each connecting area has a sleeve-shaped connecting means in the circumferential surface, the material of which loses its strength and thus its connecting property under heat transfer - here due to friction of the air flowing past. By releasing the relevant parts, the projectile in question disintegrates, the parts falling to the ground on a respective unstable trajectory.

Dieses Geschoß ist aufwendig zu fertigen. Dies wird besonders augenfällig bei einem Geschoß mit einem für Drallstabilisierung üblichen Länge/Durchmesser-Verhältnis. Außerdem ist ein Einfluß unterschiedlicher atmosphärischer Verhältnisse auf das Verhalten der Verbindungsmittel wahrscheinlich und damit nicht auszuschließen, daß die Länge der stabilen Flugbahn Schwankungen unterworfen ist. Diese dürften sich beim Übergang zu kleineren Kalibern, wie sie bei Maschinenkanonen üblich sind, besonders störend bemerkbar machen.This projectile is complex to manufacture. This is particularly evident in the case of a projectile with a length / diameter ratio which is customary for swirl stabilization. In addition, an influence of different atmospheric conditions on the behavior of the connecting means is probable and therefore it cannot be ruled out that the length of the stable trajectory is subject to fluctuations. These are likely to be particularly disruptive when switching to smaller calibers, as are common with machine guns.

Der Erfindung liegt die Aufgabe zugrunde, ein gattungsgleiches Geschoß zu schaffen, welches sich durch weniger aufwendige Fertigung und wesentlich verminderten Störeinfluß der atmosphärischen Verhältnisse auszeichnet und sich für Maschinenkanonen eignet.The invention has for its object to provide a bullet of the same type, which is characterized by less expensive production and significantly reduced interference from the atmospheric conditions and is suitable for machine guns.

Gelöst wird diese Aufgabe durch die Lehre nach dem Patentanspruch 1 mit den in seinem kennzeichnenden Teil angegebenen erfinderischen Merkmalen.This object is achieved by the teaching according to claim 1 with the inventive features specified in its characterizing part.

Die weiteren Ansprüche enthalten vorteilhafte Ausgestaltungslehren, wobei es sich als besonders vorteilhaft erweist, daß keine Beschränkungen in Abhängigkeit von der Gestaltung des Geschosses für Drall- oder Flügelstabilisierung bestehen.The further claims contain advantageous design gauges, it proving to be particularly advantageous that there are no restrictions depending on the design of the projectile for swirl or wing stabilization.

Die Erfindung wird nachstehend anhand zweier bevorzugter Ausführungsbeispiele näher erläutert.The invention is explained in more detail below with the aid of two preferred exemplary embodiments.

Es zeigen:

  • Fig.1 ein drallstabilisiertes Unterkalibergeschoß im Aufriß,
  • Fig. 1a den Heckteil des Geschosses nach Fig. 1 mit der Erfindung im längsaxialen Schnitt in größerer Darstellung,
  • Fig. 2 den Gegenstand im Querschnitt nach der Linie 11 - II in Fig. 1a,
  • Fig. 3 ein flügelstabilisiertes Unterkalibergeschoß im Aufriß und
  • Fig. 3a den Heckteil des Geschosses nach Fig. 3 mit der Erfindung, teilweise längsaxial geschnitten in größerer Darstellung.
Show it:
  • 1 shows a spin-stabilized sub-caliber floor in elevation,
  • 1a shows the rear part of the projectile according to FIG. 1 with the invention in a longitudinal axial section in a larger representation,
  • 2 shows the object in cross section along the line 11 - II in Fig. 1a,
  • Fig. 3 is a wing-stabilized lower-caliber floor in elevation and
  • Fig. 3a shows the rear part of the projectile according to Fig. 3 with the invention, partially cut longitudinally in a larger representation.

Gemäß Fig. 1 und Fig. 2 weist ein Heckteil 11 eines Geschoßkörpers 10 eines drallstabilisierten Geschosses nach Fig. 1 mit einer Umfangsfläche 12 und einer Heckfläche 14 eine rückseitige Bohrung 16 mit einer Umfangsfläche 18 und einer vorderseitigen Stirnfläche 20 auf. In letzterer ist im Bereich einer zentralen Längsachse A eine trichterförmige Zentrierbohrung 22 im Geschoßkörper 10 angeordnet. Ein im wesentlichen kreiszylindrischer Stabilisierungskörper 24 weist eine rückweitige Umfangsfläche 26 und eine konkave Heckfläche 28 auf. Zwischen einer vorderseitigen Abdrehung 32 und der rückseitigen Umfangsfläche 26 ist eine radiale Stufe 30 vorgesehen. Eine vorderseitige Stirnfläche 34 des Stabilisierungskörper 24 weist einen Zentriervorsprung 40 mit einer zentralen Bohrung 42 auf. Der Zentriervorsprung 40 paßt sich der Zentrierbohrung 22 an. Der Stabilisierungskörper 24 weist einen sich längsaxial zwischen dem Absatz 30 und der Stirnfläche 34 erstreckenden Mantel 36 mit drei radial nach außen gegen die Umfangsfläche 18 vorstehenden Zentrierrippen 38 auf. Ein jeweiliger Raum zwischen einer Umfangsfläche 39 und der rückseitigen Umfangsfläche 26 des Mantels 38 und der Umfangsfläche 18 der Bohrung 16 sowie den beiden worderseitigen Stirnflächen 20 und 24 dient einer Kreisringscheibe 54 und einem kreiszylindrischen Hohlkörper 52 eines Leuchtspursatzes 50 als Aufnahme. Den Vorsprung 40 umfängt eine Kreisringscheibe 56 einer noch zu erörtenden Substanz, die mit einer Zylinderfläche 55 der Kreisringscheibe 54 in engem Kontakt steht. Der kreiszylidrisch Hohlkörper 52 wird im betreffenden Bereich durch die Zentrierrippen 38 unterbrochen. Den heckseitigen Abschluß des Leuchtspursatzes 50 bildet ein Teil 51, das einen Raum zwischen der Heckfläche 28 und einem in der Heckfläche 14 liegenden Rand der Bohrung 16 ausfüllt. In der zentralen Bohrung 42 ist ein Draht 48 in gewendelter Form untergebracht, der mit einem vorderen Ende an einer Stelle 44 am Geschoßkörper 10 und mit einem hinteren Ende an einer Stelle 46 am Stabilisierungskörper 24 befestigt ist.1 and 2, a rear part 11 of a projectile body 10 of a spin-stabilized projectile according to FIG. 1 with a peripheral surface 12 and a rear surface 14 has a rear bore 16 with a peripheral surface 18 and a front end surface 20. In the latter, a funnel-shaped centering bore 22 is arranged in the projectile body 10 in the region of a central longitudinal axis A. An essentially circular cylindrical stabilizing body 24 has a rear circumferential surface 26 and a concave rear surface 28. A radial step 30 is provided between a front twist 32 and the rear circumferential surface 26. A front end face 34 of the stabilizing body 24 has a centering projection 40 with a central bore 42. The centering projection 40 adapts to the centering bore 22. The stabilizing body 24 has a jacket 36, which extends longitudinally axially between the shoulder 30 and the end face 34, with three centering ribs 38 projecting radially outward against the peripheral surface 18. A respective space between a circumferential surface 39 and the rear circumferential surface 26 of the jacket 38 and the circumferential surface 18 of the bore 16 and the two end faces 20 and 24 on the word side serves as an annular disk 54 and a circular cylindrical hollow body 52 of a tracer set 50. The projection 40 encircles an annular disk 56 of a substance still to be discussed, which is in close contact with a cylindrical surface 55 of the annular disk 54. The circular-cylindrical hollow body 52 is interrupted in the area in question by the centering ribs 38. The rear end of the tracer set 50 is formed by a part 51 which fills a space between the rear surface 28 and an edge of the bore 16 lying in the rear surface 14. In the central bore 42, a wire 48 is accommodated in a helical shape, which is fastened at a point 44 on the projectile body 10 and with a rear end at a point 46 on the stabilizing body 24.

Gemäß Fig. 3a weist ein Geschoßkörper 60 eines flügelstabilisierten unterkalibrigen Geschosses nach Fig. 3 ein Heckteil 62 mit einer Umfangsfläche 61 und mit einem zentral axialen Trägerfortsatz 64 vergleichsweise geringen Durchmessers auf. Eine Ausdrehfläche 64 verbindet über einen Entlastungsradius 68 die Umfangsfläche 61 mit einem Außengewinde 70 des Trägerfortsatzes 64. Letzteren umschließt - durch Gewinde formschlüssig - eine doppelwandige Büchse 72 kreiszylindrischen Querschnitts. Eine Vorderwand 74 verbindet eine Innenwand 78 mit einer Außenwand 80, wobei sich eine äußere Vorderfläche 76 der Vorderwand 74 der Ausdrehfläche 64 anschmiegt. Die Umfangsfläche 80 der Büchse 72 ist auf nicht näher dargestellte Weise mit einer dünnwandigen Hülse 86 verbunden, welche mit an ihr befestigten Stabilisierungsflügeln 88 ein Stabilisierungsleitwerk 87 bildet. Ein Hohlraum 84 zwischen einander zugewandten Fläche der Innen- 78 und der Außenwand 80 der Büchse 72 dient einem Leuchtspursatz 92 als Aufnahme, welcher sich von der Vorderwand 74 bis zu einer Heckfläche 90 erstreckt,According to FIG. 3a, a projectile body 60 of a wing-stabilized sub-caliber projectile according to FIG. 3 has a rear part 62 with a circumferential surface 61 and with a central axial support extension 64 of comparatively small diameter. An unscrewing surface 64 connects the circumferential surface 61 to an external thread 70 of the carrier extension 64 via a relief radius 68. The latter surrounds a double-walled bush 72 of circular-cylindrical cross-section in a form-fitting manner. A front wall 74 connects an inner wall 78 to an outer wall 80, an outer front surface 76 of the front wall 74 of the boring surface 64 nestling. The peripheral surface 80 of the sleeve 72 is in a manner not shown with a Connected thin-walled sleeve 86 which forms a stabilizing tail 87 with stabilizing wings 88 attached to it. A cavity 84 between the facing surface of the inner 78 and the outer wall 80 of the sleeve 72 serves as a receptacle 92, which extends from the front wall 74 to a rear surface 90,

Die Wirkungsweise der Erfindung sei zunächst an dem drallstabilisierten Geschoß nach den Figuren 1, 1a und 2 erläutert:The mode of operation of the invention is first explained on the spin-stabilized projectile according to FIGS. 1, 1a and 2:

Beim Abfeuern wird auf nicht näher zu erörternde Weise der Leuchtspursatz 50 im Bereich der Heckfläche 14 gezündet. Mit dem Teil 51 brennt auch der den Stabilisierungskörper 24 umschließende Teil 52 ab. Sobald der Abbrand des Leuchtspursatzes 50 bis zum Absatz 30 fortgeschritten ist, beginnt die Erwärmung des Mantels 36 mit dessen Zentrierrippen 38. Der Mantel 36 besteht aus einem Werkstoff, dessen Festigkeit sich durch die Einwirkung der beim Abbrand des Leuchtspursatzes 50 freiwerdenden Wärme drastisch verändert. Besteht der Mantel 36 aus einer entsprechenden Magnesiumlegierung, so verliert er seine Festigkeit infolge chemischer Umsetzung, d. h. vorzugsweise durch heftige Oxydation, welche einem Verbrauch durch Abbrand entspricht. Der Stabilisierungskörper 24 - er besteht vorteilhafterweise ebenso wie der Geschoßkörper 10 zum Verbessern der Durchschlagsleistung aus einem Werkstoff hoher Dichte, beispielsweise einer Sinterlegierung mit hohem Anteil an Wolfram oder abgereichertem Uran verliert nehmend seine Festlegung in der Bohrung. Ein entgegen der Flugrichtung 58 des Geschosses in Richtung des Pfeils 59 vorhandener Sog wirkt auf die konkave Heckfläche 28 des Stabilisierungskörpers 24. Zusätzlich wird beim Reaktionsübergang von dem Teil 54 des Leuchtspursatzes 50 auf die Substanz 56 aus dieser eine größere Gasmenge frei, die größtenteils auf die Stirnfläche 20 des Geschoßkörpers 10 und die Stirnfläche 34 des Stabilisierungskörpers 24 drückt und letzteren dabei in Richtung des Pfeils 59 axial verschiebt. Vorderseitige Druck- und rückseitige Sogwirkung lassen den Stabilisierungskörper 24 aus der Bohrung 16 heraustreten. Dabei bleibt über den sich abwickelnden Draht 48 die Verbindung zwischen dem Geschoßkörper 10 und dem Stabilisierungskörper 24 bestehen. Das betreffende System wird bei diesem Vorgang ballistisch instabil 1, verläßt seine Flugbahn und fällt nach unten. Auf diese Weise wird die letale Reichweite des betreffenden Fluggeschosses begrenzt. Der Abbrand des Leuchtspursatzes 50 und der Verbrauch des Mantels 36 sind vorteilhafterweise in weiten Grenzen zeitlich vorgebbar, so daß eine kontrollierte Begrenzung der letalen Reichweite auf einfache und zuverlässige Weise gegeben ist. Die zeitliche Einstellbarkeit der Destabilisierung der Flugbahn richtet sich dabei nach der vorgegebenen Kampfentfernung. Innerhalb derselben bleibt das System stabil, so daß beim Auftreffen auf ein Ziel die gesamte Masse aus Geschoß- und Stabilisierungskörper wirksam wird. Erst beim Überschreiten der Kampfentfernung durch Verfehlen des Zieles kommt es zu der beschriebenen Destabilisierung mit der die Reichweite des Geschosses begrenzenden Wirkung.During firing, the tracer set 50 is ignited in the region of the rear surface 14 in a manner not to be discussed in detail. With part 51, part 52 surrounding stabilizing body 24 also burns. As soon as the burn-up of the tracer set 50 has progressed to shoulder 30, the heating of the casing 36 begins with its centering ribs 38. The casing 36 consists of a material whose strength changes drastically due to the action of the heat released when the tracer set 50 is burned up. If the jacket 36 consists of a corresponding magnesium alloy, it loses its strength due to chemical reaction, i. H. preferably by violent oxidation, which corresponds to consumption by burning. The stabilizing body 24 - it advantageously consists, like the projectile body 10, of improving the penetration performance from a high-density material, for example a sintered alloy with a high proportion of tungsten or depleted uranium, increasingly losing its definition in the bore. A suction present in the direction of arrow 59 against the direction of flight 58 of the projectile acts on the concave rear surface 28 of the stabilizing body 24. In addition, during the transition from part 54 of tracer set 50 to substance 56, a larger amount of gas is released therefrom, the majority of which on the Presses the end face 20 of the projectile body 10 and the end face 34 of the stabilizing body 24 and axially shifts the latter in the direction of arrow 59. Front-side pressure and back-side suction effect let the stabilizing body 24 emerge from the bore 16. The connection between the projectile body 10 and the stabilizing body 24 remains in place over the unwinding wire 48. During this process, the system in question becomes ballistically unstable 1, leaves its trajectory and falls down. This limits the lethal range of the missile in question. The erosion of the tracer set 50 and the consumption of the jacket 36 can advantageously be predetermined within wide limits, so that there is a controlled limitation of the lethal range in a simple and reliable manner. The temporal adjustability of the destabilization of the flight path depends on the specified combat distance. The system remains stable within it, so that the entire mass of the projectile and stabilizing body becomes effective when it hits a target. Only when the combat distance is exceeded by missing the target does the described destabilization occur, with the effect of limiting the range of the projectile.

Die Wirkungsweise der Erfindung an einem flügelstabilisierten Geschoß nach der Fig. 3 und 3a wird nachstehend beschrieben:The mode of operation of the invention on a wing-stabilized projectile according to FIGS. 3 and 3a is described below:

Das Anzünden des Leuchtspursatzes 92 erfolgt abfeuerungsweise im Bereich der Heckfläche 90. Die beim Abbrand bei hoher Temperatur freiwerdende große Wärmemenge geht so wohl auf die Innen- 78 wie auch Außenwand 80 der Büchse 72 über. Während über die Außenwand 80, die Hülse 86 und die Stabilisierungsflügel 88 eine weitgehende Abführung der Wärme an die Umgebung möglich ist, entsteht im Bereich der Innenwand 78 ein starker Wärmestau. Hierdurch kommt es zur Erweichung des Werkstoffs der Innenwand 78. Sobald der Abbrand des Leuchtspursatzes 92 weit genug fortgeschritten ist, geht folglich der Formschluß zwischen der Büchse 72 und dem Trägerfortsatz 64 verloren. Das Stabilisierungsleitwerk 87 trennt sich in Richtung eines Pfeils 96 entgegen der Flugrichtung 94 vom Geschoßkörper 60 und führt dessen unmittelbarem Instabilwerden, so daß er seine ursprüngliche Flugbahn verläßt und nach unten fällt. Ober die zeitliche Einstellbarkeit der Destabilisierung gilt analog die im Zusammenhang mit dem Geschoß nach den Figuren 1a und 2 gegebene Beschreibung.The tracer 92 is ignited in the area of the rear surface 90 in a firing manner. The large amount of heat released during the burning at high temperature is transferred to the inner 78 as well as the outer wall 80 of the sleeve 72. While extensive dissipation of the heat to the surroundings is possible via the outer wall 80, the sleeve 86 and the stabilizing wings 88, a strong build-up of heat occurs in the area of the inner wall 78. As a result, the material of the inner wall 78 is softened. As soon as the burn-up of the tracer 92 has progressed far enough, the form fit between the sleeve 72 and the carrier extension 64 is lost. The stabilizing tail 87 separates from the projectile body 60 in the direction of an arrow 96 opposite to the direction of flight 94 and causes it to become immediately unstable, so that it leaves its original trajectory and falls down. The description given in connection with the projectile according to FIGS. 1a and 2 applies analogously to the temporal adjustability of the destabilization.

Da die Stabilisierungsflügel üblicherweise eine geringe Anstellung zum Erzeugen einer leichten Ausgleichsdrehung aufweisen, wird hierdurch die Abtrennung vom Geschoß gemäß der Erfindung zusätzlich begünstigt.Since the stabilizing wings usually have a low pitch for generating a slight compensating rotation, this additionally favors the separation from the projectile according to the invention.

Bei vorgeschlagenen Lösungen soll eine Zerlegerladung nach einer vorgegebenen Zeit über einen Leuchtspursatz initiiert werden. Dabei ergeben sich erhebliche Nachteile: die Zerlegerladung kann bereits im Rohr betätigt werden und hierdurch das Waffensystem empfindlich schädigen oder unbrauchbar machen. Die Zerlegerladung bedarf einer zentralaxialen Bohrung zu ihrer Aufnahme. Diese Bohrung mindert die Durchschlagsleistung des Geschosses bei gepanzerten Zielen. Um ausreichende Wirkung zu gewährleisten, muß die Zerlegerladung eine bestimmte Mindestgröße aufweisen. Hierdurch wird die Dichte des Geschosses beeinträchtigt.In the case of proposed solutions, a fragmentation charge is to be initiated via a tracer set after a predetermined time. This has considerable disadvantages: the fragmentation charge can already be actuated in the barrel, thereby damaging the weapon system or making it unusable. The fragmentation charge requires a central axial bore to accommodate it. This hole reduces the penetration rate of the projectile on armored targets. To ensure sufficient effectiveness, the fragmentation charge must have a certain minimum size. This affects the density of the projectile.

Sämtliche aufgezählten Nachteile werden durch die Erfindung mit Sicherheit vermieden. Selbst bei einem fehlerhaften Leuchtspursatz verläßt das Gesamtgeschoß das Rohr und das Waffensystem bleibt einsatzbereit.All of the disadvantages listed are definitely avoided by the invention. Even with a faulty tracer set, the entire floor leaves the barrel and the weapon system remains ready for use.

Claims (10)

1. Projectile with a projectile body (10, 60), a stabilizing element (24, 87) and a connection means (36, 72), formed of a material which, under the effect of heat transfer thereto, loses its strength and thus its connective property so that the projectile, by the detachment of at least one part (24, 87) from its original position becomes unstable whereby the lethal range becomes limited, characterized by the fact that the projectile body (10, 60) comprises mainly one single piece and the connection means (36, 72) by which the stabilizing element (24, 87) is secured to the projectile body (10, 60) is in direct contact with a tracer composition (50, 92) for the transference of the reaction heat.
2. Projectile in accordance with Claim 1, characterized by the fact that the stabilizing element (24) is positioned, as a rotationally symmetrical body, with a casing (36) surrounding it, with centering means (38) in a rear boring (16) of the projectile body (10), in order to receive a tracer (50) in such a way that the casing (36), as a connection means, is surrounded by the tracer (50), a second connection means (48) being provided which enables same to be detached from the original position while maintaining the connection with the projectile body (10).
3. Projectile in accordance with Claim 2, characterized by the fact that the second connection means (48) takes the form of a wire.
4. Projectile in accordance with Claim 2 or 3, characterized by a centering bore (22) in a front end surface (22) of the bore (16) and by a centering projection (40) corresponding thereto and provided on a front end surface (34) of the stabilizing element (24).
5. Projectile in accordance with Claim 3 or 4, characterized by the fact that the centering projection (40) is constructed as a receiver for a wire (48) and the rear securing means therefor (46) on the stabilizing element (24), and in the centering bore (22) of the wire (48) there is provided at (44) a front securing means to the projectile body (10).
6. Projectile in accordance with any one of Claims 2 to 5, characterized by a concave tail surface (28) of the stabilizing element (24).
7. Projectile in accordance with any one of Claims 2 to 6, characterized by the fact that the rear part of the stabilizing element (24) is completely covered by the tracer composition (50).
8. Projectile in accordance with any one of Claims 2 to 7, characterized by the fact that the tracer composition has a circular annular portion (54) which concentrically, with a distance between an inner surface (55) and an outer surface of the centering projection (40), covers the outer zone of the front end surface (34) of the stabilizing element (24), and surrounds a body (56) from the bulk of which, on the transference of the reaction heat from the tracer composition (50, 54), a quantity of gas is released which acts both on the end surface (20) in the bore (16) and on the end surface (34) of the stabilizing element (24), in order to assist in detaching it from its original position.
9. Projectile in accordance with at least one of Claims 1 to 8, characterized by the fact that the material both of the projectile body (10, 60) and of the stabilizing element (24) has a high density.
10. Projectile in accordance with Claim 1, characterized by the following features:
(a) the stabilizing element is constructed as a stabilizing tail (87),
(b) the connection means is constructed as a rotationally symmetrical sleeve (72) with an inner wall (78), an outer wall (80) and a front communicating wall (74), with a hollow space (84) as a receiver for the tracer composition (92),
(c) by an internal threading the sleeve (72) is interlockingly connected on the form-closed principle with an external threading (70) of a supporting extension (74) on the tail of the projectile body (60),
(d) an outer peripheral surface (80) of the sleeve (72) bears a thin-walled casing (86), with stabilizing fins (88) attached to this latter.
EP82110864A 1981-11-25 1982-11-24 Tracer projectile, preferably for machine guns, with range reducing device Expired EP0080210B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82110864T ATE35051T1 (en) 1981-11-25 1982-11-24 AMMUNITION, PREFERABLE FOR MACHINE CANNONS, WITH A FLARE RATIO, WHICH LIMITED THE LETHAL RANGE WHEN MISSING A TARGET.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19813146645 DE3146645A1 (en) 1981-11-25 1981-11-25 DEVICE FOR THE CONTROLLED LIMITATION OF THE LETAL RANGE OF A TARGET MISSING A TARGET WITH A STABILIZING ELEMENT AND A LUMINAIRE TRACK
DE3146645 1981-11-25

Publications (3)

Publication Number Publication Date
EP0080210A2 EP0080210A2 (en) 1983-06-01
EP0080210A3 EP0080210A3 (en) 1984-02-22
EP0080210B1 true EP0080210B1 (en) 1988-06-08

Family

ID=6147139

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82110864A Expired EP0080210B1 (en) 1981-11-25 1982-11-24 Tracer projectile, preferably for machine guns, with range reducing device

Country Status (4)

Country Link
US (1) US4519316A (en)
EP (1) EP0080210B1 (en)
AT (1) ATE35051T1 (en)
DE (1) DE3146645A1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3565891D1 (en) * 1984-07-17 1988-12-01 Eidgenoess Munitionsfab Thun Missile for practice ammunition having a limited range, and use of the same
DE3613866A1 (en) * 1986-04-24 1987-10-29 Rheinmetall Gmbh RANGE-LIMITED, ARROW-STABILIZED SUB-CALIBAR FLOOR FOR A TUBE ARM
US4682546A (en) * 1986-10-02 1987-07-28 Chovich Milija M Projectile
BR8707548A (en) * 1986-11-28 1989-03-14 Royal Ordnance Plc TUBULAR PROJECTILE, CONSTRUCTION FOR LAUNCHING A PROJECTILE, FLEXIBLE GLOVE FOR INCORPORATION IN A PROJECTIL'S CAVITY AND A PROJECTILE MANUFACTURING PROCESS
DE3732372C1 (en) * 1987-09-25 1994-12-22 Rheinmetall Gmbh Wing-stabilised projectile
DE3927799A1 (en) * 1989-08-23 1991-02-28 Rheinmetall Gmbh Reducing practice projectile range by thermally induced expansion - of hollow sheet metal fins
FR2739683B1 (en) * 1995-10-05 1997-12-05 France Etat LABEL TYPE KINETIC ENERGY EXERCISE PROJECTILE
US9157713B1 (en) 2013-03-15 2015-10-13 Vista Outdoor Operations Llc Limited range rifle projectile

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NL2171C (en) * 1914-04-18
FR49651E (en) * 1925-03-05 1939-05-30 Method of propulsion within a fluid, and devices for implementing this method
DE1428678C3 (en) * 1964-12-24 1974-04-11 Dynamit Nobel Ag, 5210 Troisdorf Training grenade
BE789868A (en) * 1971-10-11 1973-02-01 Mefina Sa INSTANT SELF-DESTRUCTION MECHANICAL ROCKET WITH DETONATOR AND TRACK SAFETY
NL7705239A (en) * 1977-05-11 1978-11-14 Eurometaal Nv EXERCISE PROJECTILE OF THE TYPE WITH A LOOSE CUFF.
DE2747313C2 (en) * 1977-10-21 1983-01-20 Rheinmetall GmbH, 4000 Düsseldorf Sub-caliber arrow projectile with a resistance-stabilizing conical tail section
DE2756420C2 (en) * 1977-12-17 1985-02-07 Rheinmetall GmbH, 4000 Düsseldorf Bullet with automatic splitting effect
DE2844870C2 (en) * 1978-10-14 1984-10-18 Rheinmetall GmbH, 4000 Düsseldorf Sub-caliber training projectile
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NL8200221A (en) * 1981-02-12 1982-09-01 Diehl Gmbh & Co Sub-calibre projectile with control surface - has surface-separation device functioning after set time

Also Published As

Publication number Publication date
DE3146645A1 (en) 1983-06-01
US4519316A (en) 1985-05-28
ATE35051T1 (en) 1988-06-15
EP0080210A3 (en) 1984-02-22
EP0080210A2 (en) 1983-06-01
DE3146645C2 (en) 1989-02-16

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