EP0157112A1 - Fin-stabilised projectile - Google Patents

Fin-stabilised projectile Download PDF

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Publication number
EP0157112A1
EP0157112A1 EP85101125A EP85101125A EP0157112A1 EP 0157112 A1 EP0157112 A1 EP 0157112A1 EP 85101125 A EP85101125 A EP 85101125A EP 85101125 A EP85101125 A EP 85101125A EP 0157112 A1 EP0157112 A1 EP 0157112A1
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EP
European Patent Office
Prior art keywords
projectile
stop
wing
fin
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.)
Withdrawn
Application number
EP85101125A
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German (de)
French (fr)
Inventor
Rolf Hellwig
Klaus Dietmar Karius
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 EP0157112A1 publication Critical patent/EP0157112A1/en
Withdrawn legal-status Critical Current

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    • 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
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • the invention relates to a wing-stabilized projectile according to the preamble of patent claim 1.
  • Bullets with foldable stabilizing wings are already known from DE-PS 960 882.
  • a tail unit attached to the rear of the storey can best develop its aerodynamic effect if it lies largely in the undisturbed air flow. During flight, it must therefore protrude as far as possible beyond the projectile diameter, while it must be folded when the projectile passes through the projectile. According to the known solution, this is brought about by a control element in the form of a hollow piston which is pivoted out in a cylinder bore in the rear of the projectile, thereby spreading the initially adjacent wings and securing them in this position.
  • the piston has cone-shaped control surfaces, on which correspondingly bevelled surfaces of the wing ends come to rest, and collars that protrude beyond the diameter, on the one hand spread the wings and prevent them from collapsing after spreading. Due to the necessary control surfaces and control collars, the manufacture of this tail unit is comparatively complex.
  • Another disadvantage is that the hollow piston is actuated by the gas pressure, and that for its actuation precisely coordinated holes to the chamber in the rear part of the projectile are necessary, in which the hollow piston is slidably mounted.
  • the object of the invention is to provide a wing-stabilized projectile which is considerably simplified with respect to the tail unit, but which is nevertheless of robust construction and withstands the highest launch accelerations.
  • Fig. 1 shows a side view of a projectile 10 with a projectile body 11, the rear part of which is shown as a longitudinal section.
  • the projectile 10 is wing-stabilized and for this purpose has an empennage with fold-out wings 14.
  • These wings 14 are arranged in the rear part of the projectile body 11 in such a way that they do not protrude from the outer contour of the projectile body 11 when they are folded and do not unfold until the projectile 11 has left the weapon barrel.
  • Each wing 14 is pivotally mounted about an axis of rotation 14 ′ arranged perpendicular to the longitudinal axis of the projectile body 11.
  • the projectile body 11 is closed at the rear by a wing stop 15 which is fastened to the projectile body 11 so as to be rotatable about the longitudinal axis of the projectile.
  • the wing stop 15 is acted upon by a torsion spring 13 which is supported on the one hand on the wing stop 15 and on the other hand on the projectile body 11.
  • a groove 16 is arranged in the wing stop 15 for each wing 14 (FIG. 2), into which the wing 14 engages in the folded position, which is also shown in broken lines in FIG. 1.
  • the wings 14 unfold as a result of the centrifugal force arising from the swirl of the projectile 10.
  • the projectile 10 is fired with a certain twist, which is transmitted primarily to the projectile body 11 by the guide band 12 arranged in the rear part of the projectile 10.
  • the wing stop 14 acted upon by the torsion spring 13 rotates by a certain angle around the longitudinal axis of the projectile 10 until it is released by a stop pin 17, which is inserted into the rear part of the projectile body 11 and into one arranged in the wing stop 15 Groove 17 'engages, is stopped.
  • the grooves 16 are rotated in relation to the wings 14 in such a way that the wings can no longer be folded in since they are now rest firmly on the wing stop 15. In this way, a particularly secure locking of the wings 14 is achieved without the need for particularly complex shaped projecting collars, as would be necessary in the prior art.
  • the wing arrangement proposed according to the invention is distinguished by a particularly simple construction which enables inexpensive mass production. Despite its simplicity, it is particularly reliable because it works completely independently of the gas pressure. Finally, the arrangement is also extremely robust and withstands the highest acceleration values, since no parts which are movable in the longitudinal axial direction and which are particularly susceptible to acceleration forces acting primarily in the longitudinal axis direction are necessary for the actuation of the wings 14 and their locking.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Abstract

A fin-stabilised projectile has swing-out fins (14) which are arranged in the tail part of the projectile body (11) and which are swung in during the course of the projectile (10) through the barrel and at the same time engage in radial grooves of a fin stop (15) arranged in the tail part of the projectile (10). The fin stop (15) is mounted rotatably in the tail part of the projectile body (11) and is loaded in the direction of rotation by a torsion spring (13). After the projectile (10) has been fired, the fins (14) are deployed as a result of the centrifugal force occurring in response to the rotation of the projectile body (11). Thereupon, the fin stop (15) loaded by the torsion spring (13) can rotate so that the fins (14) now rest outside the radial grooves on the surface of the fin stop (15), thus reliably preventing them from being swung in again undesirably. <IMAGE>

Description

Die Erfindung betrifft ein flügelstabilisiertes Geschoß nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a wing-stabilized projectile according to the preamble of patent claim 1.

Geschosse mit klappbaren Stabilisierungsflügeln sind aus der DE-PS 960 882 bereits bekannt. Ein am Heck des Geschosses angebrachtes Leitwerk entfaltet seine aerodynamische Wirkung am besten, wenn es weitgehend in der ungestörten Luftströmung liegt. Während des Flugs muß es daher möglichst weit über den Geschoßdurchmesser hinausragen, während es beim Rohrdurchlauf des Geschosses zusammengeklappt sein muß. Gemäß der bekannten Lösung wird dies durch ein Steuerelement in Form eines Hohlkolbens bewirkt, der in einer Zylinderbohrung im Geschoßheck ausgeschwenkt wird, dabei die zunächst anliegenden Flügel gleichzeitig spreizt und sie in dieser Lage sichert. Dazu verfügt der Kolben über konusförmig ausgebildete Steuerflächen, auf die entsprechend angeschrägte Flächen der Flügelenden zur Anlage kommen und über den Durchmesser hinausstehende Bunde die einerseits die Flügel ausspreizen und nach Ausspreizen ein Zusammenklappen verhindern. Aufgrund der notwendigen Steuerflächen und Steuerbunde ist die Herstellung dieses Leitwerks vergleichsweise aufwendig. Ein weiterer Nachteil besteht darin, daß der Hohlkolben durch den Gasdruck betätigt wird, und daß für dessen Betätigung genau abgestimmte Bohrungen zu der Kammer im Heckteil des Geschosses notwendig sind, in dem der Hohlkolben gleitbar gelagert ist.Bullets with foldable stabilizing wings are already known from DE-PS 960 882. A tail unit attached to the rear of the storey can best develop its aerodynamic effect if it lies largely in the undisturbed air flow. During flight, it must therefore protrude as far as possible beyond the projectile diameter, while it must be folded when the projectile passes through the projectile. According to the known solution, this is brought about by a control element in the form of a hollow piston which is pivoted out in a cylinder bore in the rear of the projectile, thereby spreading the initially adjacent wings and securing them in this position. For this purpose, the piston has cone-shaped control surfaces, on which correspondingly bevelled surfaces of the wing ends come to rest, and collars that protrude beyond the diameter, on the one hand spread the wings and prevent them from collapsing after spreading. Due to the necessary control surfaces and control collars, the manufacture of this tail unit is comparatively complex. Another disadvantage is that the hollow piston is actuated by the gas pressure, and that for its actuation precisely coordinated holes to the chamber in the rear part of the projectile are necessary, in which the hollow piston is slidably mounted.

Der Erfindung liegt die Aufgabe zugrunde, ein hinsichtlich des Leitwerks wesentlich vereinfachtes flügelstabilisiertes Geschoß anzugeben, das dennoch robust aufgebaut ist und höchsten Abschußbeschleunigungen standhält.The object of the invention is to provide a wing-stabilized projectile which is considerably simplified with respect to the tail unit, but which is nevertheless of robust construction and withstands the highest launch accelerations.

Diese Aufgabe wird durch die in Patentanspruch 1 angegebene Erfindung gelöst.This object is achieved by the invention specified in claim 1.

Vorteilhafte Ausgestaltungen der Erfindung gehen aus den Unteransprüchen hervor.Advantageous embodiments of the invention emerge from the subclaims.

Die Erfindung wird nachfolgend unter Bezug auf die Zeichnungen näher erläutert.The invention is explained in more detail below with reference to the drawings.

Dabei zeigt:

  • Fig. 1: eine Seitenansicht des Geschosses, bei der das Heck teilweise im Längsschnitt dargestellt ist;
  • Fig. 2: eine Ansicht auf die Heckseite des Geschosses mit den Flügeln in ausgeklappter Stellung.
It shows:
  • Fig. 1: a side view of the projectile, in which the rear is partially shown in longitudinal section;
  • Fig. 2: a view of the rear side of the projectile with the wings in the extended position.

Fig. 1 zeigt in Seitenansicht ein Geschoß 10 mit einem Geschoßkörper 11, dessen Heckteil als Längsschnitt dargestellt ist. Das Geschoß 10 ist flügelstabilisiert und verfügt zu diesem Zweck über ein Leitwerk mit ausklappbaren Flügeln 14.Fig. 1 shows a side view of a projectile 10 with a projectile body 11, the rear part of which is shown as a longitudinal section. The projectile 10 is wing-stabilized and for this purpose has an empennage with fold-out wings 14.

Diese Flügel 14 sind derart im Heckteil des Geschoßkörpers 11 angeordnet, daß sie während des Rohrdurchlaufs eingeklappt nicht über die Außenkontur des Geschoßkörpers 11 hinausragen und sich erst dann entfalten, nachdem das Geschoß 11 das Waffenrohr verlassen hat. Jeder Flügel 14 ist um eine senkrecht zur Längsachse des Geschoßkörpers 11 angeordnete Drehachse 14' schwenkbar gelagert. Der Geschoßkörper 11 wird heckseitig von einem Flügelanschlag 15 abgeschlossen, der um die Längsachse des Geschosses drehbar am Geschoßkörper 11 befestigt ist. Der Flügelanschlag 15 ist durch eine Drehfeder 13 beaufschlagt, die sich einerseits am Flügelanschlag 15 und andererseits am Geschoßkörper 11 abstützt. Im Flügelanschlag 15 ist für jeden Flügel 14 eine Nut 16 angeordnet (Fig. 2), in die der Flügel 14 in eingeklappter Stellung, die in Fig. 1 strichliert ebenfalls dargestellt ist, einrastet. Nach Abschuß des Geschosses 10 entfalten sich die Flügel 14 infolge der durch Drall des Geschosses 10 auftretenden Zentrifugalkraft. Das Geschoß 10 wird dazu mit einem bestimmten Drall abgeschossen, der vornehmlich durch das im Heckteil des Geschosses 10 angeordnete Führungsband 12 auf den Geschoßkörper 11 übertragen wird. Unmittelbar nach dem Ausklappen der Flügel 14 rotiert der von der Drehfeder 13 beaufschlagte Flügelanschlag 14 um einen gewissen Winkelwert um die Längsachse des Geschosses 10, bis er von einem Anschlagstift 17, der in das Heckteil des Geschoßkörpers 11 eingesetzt ist und in eine im Flügelanschlag 15 angeordnete Nut 17' eingreift, angehalten wird. Infolge dieser Drehbewegung des Flügelanschlags 15 werden die Nuten 16 derart in bezug auf die Flügel 14 verdreht, daß ein Einklappen der Flügel nicht mehr möglich ist, da sie jetzt fest auf dem Flügelanschlag 15 aufliegen. Auf diese Weise wird eine besonders sichere Arretierung der Flügel 14 erreicht, ohne daß dazu besonders kompliziert geformte vorspringende Bunde, wie beim Stand der Technik notwendig wären. Die erfindungsgemäß vorgeschlagene Flügelanordnung zeichnet sich durch eine besonders einfache Konstruktion aus, die eine preiswerte Massenherstellung ermöglicht. Trotz ihrer Einfachheit ist sie besonders zuverlässig, da sie völlig unabhängig vom Gasdruck funktioniert. Schließlich ist die Anordnung auch noch extrem robust und hält höchsten Beschleunigungswerten stand, da für die Betätigung der Flügel 14 und deren Arretierung keine' in Längsaxialrichtung beweglichen Teile notwendig sind, die gegenüber vornehmlich in Längsachsenrichtung angreifenden Beschleunigungskräften besonders anfällig sind.These wings 14 are arranged in the rear part of the projectile body 11 in such a way that they do not protrude from the outer contour of the projectile body 11 when they are folded and do not unfold until the projectile 11 has left the weapon barrel. Each wing 14 is pivotally mounted about an axis of rotation 14 ′ arranged perpendicular to the longitudinal axis of the projectile body 11. The projectile body 11 is closed at the rear by a wing stop 15 which is fastened to the projectile body 11 so as to be rotatable about the longitudinal axis of the projectile. The wing stop 15 is acted upon by a torsion spring 13 which is supported on the one hand on the wing stop 15 and on the other hand on the projectile body 11. A groove 16 is arranged in the wing stop 15 for each wing 14 (FIG. 2), into which the wing 14 engages in the folded position, which is also shown in broken lines in FIG. 1. After the projectile 10 has been fired, the wings 14 unfold as a result of the centrifugal force arising from the swirl of the projectile 10. The projectile 10 is fired with a certain twist, which is transmitted primarily to the projectile body 11 by the guide band 12 arranged in the rear part of the projectile 10. Immediately after the wings 14 have been unfolded, the wing stop 14 acted upon by the torsion spring 13 rotates by a certain angle around the longitudinal axis of the projectile 10 until it is released by a stop pin 17, which is inserted into the rear part of the projectile body 11 and into one arranged in the wing stop 15 Groove 17 'engages, is stopped. As a result of this rotary movement of the wing stop 15, the grooves 16 are rotated in relation to the wings 14 in such a way that the wings can no longer be folded in since they are now rest firmly on the wing stop 15. In this way, a particularly secure locking of the wings 14 is achieved without the need for particularly complex shaped projecting collars, as would be necessary in the prior art. The wing arrangement proposed according to the invention is distinguished by a particularly simple construction which enables inexpensive mass production. Despite its simplicity, it is particularly reliable because it works completely independently of the gas pressure. Finally, the arrangement is also extremely robust and withstands the highest acceleration values, since no parts which are movable in the longitudinal axial direction and which are particularly susceptible to acceleration forces acting primarily in the longitudinal axis direction are necessary for the actuation of the wings 14 and their locking.

Claims (3)

1. Flügelstabilisiertes Geschoß mit im Heckteil des Geschosses angeordneten, um senkrecht auf der Geschoßlängsachse liegenden Drehachsen gelagerten Flügeln, dadurch gekennzeichnet, daß im Heckbereich des Geschosses (10) und relativ zu diesem verdrehbar, ein Flügelanschlag (15) mit in Radialrichtung eingebrachten Nuten (16) vorgesehen ist, in die die Flügel (14) im eingeklappten Zustand eintauchen und auf dem die Flügel (14) im ausgeklappten Zustand aufliegen.1. Wing-stabilized projectile with wings arranged in the rear part of the projectile and mounted about vertical axes of rotation lying on the longitudinal axis of the projectile, characterized in that in the rear region of the projectile (10) and rotatable relative to the latter, a wing stop (15) with radial grooves (16 ) is provided, into which the wings (14) are immersed in the folded state and on which the wings (14) rest in the unfolded state. 2. Geschoß nach Anspruch 1, dadurch gekennzeichnet, daß der Flügelanschlag (15) durch eine Drehfeder (13) beaufschlagt ist, die einerseits am Flügelanschlag 15 und andererseits am Geschoßkörper (11) des Geschosses (10) angreift.2. Projectile according to claim 1, characterized in that the wing stop (15) is acted upon by a torsion spring (13) which engages on the one hand on the wing stop 15 and on the other hand on the projectile body (11) of the projectile (10). 3. Geschoß nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß zur Begrenzung der Drehbewegung des Flügelanschlags (15) ein Anschlagstift (17) vorgesehen ist, der im Heckteil des Geschoßkörpers (11) gelagert ist und in eine im Flügelanschlag (15) angeordnete Nut (18') eingreift.3. Projectile according to one of claims 1 and 2, characterized in that a stop pin (17) is provided to limit the rotational movement of the wing stop (15), which is mounted in the rear part of the projectile body (11) and in a in the wing stop (15) arranged groove (18 ') engages.
EP85101125A 1984-03-09 1985-02-04 Fin-stabilised projectile Withdrawn EP0157112A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843408585 DE3408585A1 (en) 1984-03-09 1984-03-09 WING STABILIZED SHELL
DE3408585 1984-03-09

Publications (1)

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EP0157112A1 true EP0157112A1 (en) 1985-10-09

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EP85101125A Withdrawn EP0157112A1 (en) 1984-03-09 1985-02-04 Fin-stabilised projectile

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DE (1) DE3408585A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3631277C1 (en) * 1986-09-13 1987-12-10 Messerschmitt Boelkow Blohm Empennage (set of control surfaces) for missiles
US4796835A (en) * 1986-12-17 1989-01-10 The Marquardt Company Projectile
US4752052A (en) * 1986-12-17 1988-06-21 The Marquardt Company Projectile
DE19906969B4 (en) * 1999-02-19 2004-10-14 Rheinmetall W & M Gmbh Tail-stabilized projectile that can be fired from a weapon barrel
DE10015514B4 (en) * 2000-03-30 2007-10-04 Rheinmetall Waffe Munition Gmbh Wing stabilized projectile

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1187193A (en) * 1957-11-15 1959-09-08 Hotchkiss Brandt Deployable stabilizer for projectile
GB2121147A (en) * 1982-06-02 1983-12-14 British Aerospace Missile fin assemblies
DE3222378A1 (en) * 1982-06-15 1983-12-15 Dynamit Nobel Ag, 5210 Troisdorf Device for reducing the sensitivity to lateral onflow of tail-stabilised combat bodies moving in air and/or water

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1187193A (en) * 1957-11-15 1959-09-08 Hotchkiss Brandt Deployable stabilizer for projectile
GB2121147A (en) * 1982-06-02 1983-12-14 British Aerospace Missile fin assemblies
DE3222378A1 (en) * 1982-06-15 1983-12-15 Dynamit Nobel Ag, 5210 Troisdorf Device for reducing the sensitivity to lateral onflow of tail-stabilised combat bodies moving in air and/or water

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Publication number Publication date
DE3408585A1 (en) 1985-09-12

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Inventor name: KARIUS, KLAUS DIETMAR