EP2339285B1 - Grenade and grenade launching device - Google Patents

Grenade and grenade launching device Download PDF

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Publication number
EP2339285B1
EP2339285B1 EP10015602.5A EP10015602A EP2339285B1 EP 2339285 B1 EP2339285 B1 EP 2339285B1 EP 10015602 A EP10015602 A EP 10015602A EP 2339285 B1 EP2339285 B1 EP 2339285B1
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EP
European Patent Office
Prior art keywords
shell
grenade
flow cross
firing
base body
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EP10015602.5A
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German (de)
French (fr)
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EP2339285A3 (en
EP2339285B8 (en
EP2339285A2 (en
Inventor
Helmut Hammer
Axel Pfersmann
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Diehl Defence GmbH and Co KG
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Diehl BGT Defence GmbH and Co KG
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Publication of EP2339285B1 publication Critical patent/EP2339285B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A1/00—Missile propulsion characterised by the use of explosive or combustible propellant charges
    • F41A1/08—Recoilless guns, i.e. guns having propulsion means producing no recoil
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/08—Ordnance projectiles or missiles, e.g. shells
    • F42B30/10—Mortar projectiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/10—Cartridges, i.e. cases with charge and missile with self-propelled bullet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F42C19/0826—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition comprising an elongated perforated tube, i.e. flame tube, for the transmission of the initial energy to the propellant charge, e.g. used for artillery shells and kinetic energy penetrators

Definitions

  • the invention relates to a rohrgehitbare grenade according to the preamble of claim 1 and a grenade launcher with such a grenade.
  • Such a grenade is from the US 2 671 401 known,
  • a known concept for achieving a recoil-free launch of a grenade from a grenade launcher is that the grenade launcher consists of a tube open on both sides which has no flow cross-sectional constrictions. Ideally, not only the amount of the flow cross-sectional area over the entire tube length is constant, but also the shape of the flow cross-sectional area. For example, the flow cross-sectional area over the entire tube length on a circular disk shape with a constant radius. This ensures that no axial forces are transmitted to the tube when the grenade is fired. The propellant gases of the grenade being launched can leave the tube of the grenade launcher unhindered to the rear.
  • the momentum of the forward accelerated grenade corresponds exactly to the momentum of the propellant gases leaving the tube to the rear.
  • this concept has the advantage that with a relatively simple design of the grenade launcher in a simple manner recoilless launching a tubular mortar can be achieved, but the concept has the disadvantage that the resulting after ignition of the propellant gas pressure very quickly backwards through the open pipe end flows out. The propulsive effect on the grenade to be fired is therefore only slight.
  • the invention is based on the idea that a flow cross-sectional constriction in the launch tube can in principle prevent too rapid outflow of the gas pressure arising when the propellant burns, which ultimately improves the propulsive effect on the shell body.
  • a flow cross-section reduction device which is not fixedly connected to the launching tube, but is spaced from it by a connecting device with the grenade base body and is connected in a fire-stable manner.
  • the grenade base body preferably has a cylindrical shape whose outer diameter substantially corresponds to the inner diameter of the launching tube.
  • the grenade body has on its lateral surface sealing means which are suitable to seal gaps between the lateral surface of the grenade body and the inner surface of the launching tube. This can prevent propellant charge gases from leaving the launching tube at the front of the grenade body, which would lead to a reduction of the propulsion effect on the grenade.
  • the flow cross-section reduction device comprises a hollow cylindrical ring, which is connected via one or more webs to the connecting device. In this way, a lightweight, yet stable construction of the flow cross-section reduction device can be ensured.
  • the outer diameter of the ring at least over a portion of the height of the hollow cylinder corresponds to the outer diameter of the cylindrical grenade body. This improves the guidance of the tubular grenade and avoids jamming of the grenade in the launching tube.
  • edges of the webs and / or the ring are beveled on the side facing the grenade body.
  • an aerodynamically favorable flow of the webs and / or the ring is achieved by the propellant charge gases.
  • the walls of the webs and / or the ring are formed such that the cavities between them have a nozzle shape.
  • an improved thrust on the grenade can be achieved.
  • a particularly good thrust effect is achieved when the nozzle shape is that of a Laval nozzle.
  • the flow cross-section reduction device preferably has the shape of a ring guide. This has the advantage that the grenade is flight stabilized after leaving the tube.
  • the connecting device comprises an extension tube extending in extension to the cylinder longitudinal axis of the grenade body.
  • This launch tube includes a base charge.
  • the base charge may represent the middle part of a detonating chain, which includes Matterzündladung, base charge and main charge.
  • the starting pipe has radial bores which allow over-ignition of the ignited basic charge to a main charge which can be arranged annularly around the starting pipe and between the grenade base body and the flow cross-section reduction means.
  • These overflow holes of the starting pipe can be sealed with a brass foil. After reaching the bursting pressure of the brass foil, the main charge is ignited by the combustion gases flowing out of the overflow holes of the base charge.
  • the flow cross-section reduction device carries a wired data link which can be developed during the firing of the grenade and connects the grenade to a fire control computer at least until it leaves the launching tube or during the initial flight phase of the grenade after leaving the launching tube.
  • the unwindable wire of the data link is arranged on the flow cross-section reduction device in such a way that the wire is subjected as little as possible to the hot powder gases and particles formed when the grenade is fired. As a result, it can be ensured in an advantageous manner that the wire of the data link does not tear when the grenade is launched.
  • the wire is wound in a coil shape around the ring in a hollow cylinder-shaped gap between outer diameter of the ring and inner surface of the launching tube that is open only against the firing direction.
  • the wire is particularly well protected by the hot powder gases resulting from the launch of the grenade and at the same time ensures easy unwindability of the wire.
  • the present invention also includes a grenade launcher having a grenade as described above.
  • the grenade launcher has a tube open on both sides without flow cross-sectional constrictions.
  • the tube of the grenade launcher is closed at its front and / or rear end before the launch of the grenade with a lid.
  • the rear lid is connected to the grenade via a holding device which is arranged to hold the grenade in a rear position in the tube before launching. This will prevent the grenade from slipping back and forth in the tube before launching. In particular, during transport of the grenade launcher thus damage the grenade located in it can be avoided.
  • the rear cover is configured to burst under the action of the build-up gas pressure of the main charge of the shell to release the rear end of the tube. In this way it can be ensured that the protective effect of the lid is maintained as long as possible.
  • the holding device via which the rear cover is connected to the shell, has a predetermined breaking point, at which the holding device breaks during acceleration of the shell. In this way, the initiation of axial forces into the grenade launcher upon launch of the grenade can be minimized.
  • FIGS. 1 a and 1 b show a tubular shell grenade 1, which comprises a shell body 10.
  • the grenade comprises a flow cross-section reduction device 12, which in relation to the grenade main body 10 in the opposite direction to the firing direction X of Grenade 1 is arranged.
  • the flow cross-section reduction device 12 is spaced apart from the grenade base body 10 via a connecting device 13 with the grenade main body 10 and connected in a stable manner to the launch.
  • This grenade 1 can recoilless be fired from a tube 2 open on both sides.
  • the inventive design of the flow cross-section reduction device 12 ensures that no axial forces are introduced into the grenade launcher when the grenade 1 is launched. At the same time, this ensures that the flow cross-section of the launching tube 2 is reduced, as a result of which a too rapid outflow of the gas pressure when the shell 1 is fired is prevented.
  • FIGS. 1a and 1b Granat ground stresses 10 shown a cylindrical shape.
  • the outer diameter of this cylindrical shape preferably corresponds substantially to the inner diameter of the launching tube 2, from which the shell 1 is fired.
  • the shell body 10 has at least one sealing ring 14 on its lateral surface. By means of these sealing rings gaps between the lateral surface of the grenade body 10 and the inner surface of the launching tube 2 can be sealed.
  • the flow cross-section reduction device 12 comprises a hollow cylindrical ring 12a. This ring 12a is connected to the connecting device 13 via one or more webs 12b.
  • the outer diameter of the ring 12a corresponds to the grenade base body 10 side facing the outer diameter of the cylindrical grenade body 10.
  • the ring 12a tapers to a hollow cylindrical ring with a slightly smaller radius.
  • the edges of the webs 12b and the ring 12a are beveled on the grenade base body 10 facing side.
  • the walls of the webs 12b and 12a of the ring are formed such that the cavities between them have a nozzle shape.
  • the flow cross-section reduction device 12 has the shape of a ring guide.
  • the connecting device 13 comprises a tube extending in extension to the cylinder longitudinal axis of the grenade main body 10. This tube 13 contains a basic charge 15.
  • the tube 13 has radial bores 16, which can be ignited by the ignited base charge 15 onto a main charge 17 that can be arranged annularly around the starting tube and between the grenade base body 10 and the flow cross-section reduction device 12 enable.
  • This main charge 17 may include one or more perforated discs of propellant material through which the tube 13 protrudes.
  • the grenade launcher has a tube 2 open on both sides without flow cross-sectional constrictions.
  • a grenade 1 is mounted, as described above and below.
  • the flow cross-section reduction device 12 is embodied as a carrier of a wired data link 18 that can be developed during the firing of the grenade 1.
  • This data link 18 connects the grenade 1 at least until leaving the launching tube 2 or in the initial flight phase of the grenade 1 after leaving the launching tube 2 with a Feuerleitrechner (not shown).
  • the wire 18 is wound around the ring 12a in a coil shape around the ring 12a in a hollow cylinder-shaped gap between outer diameter of the ring 12a and inner surface of the launch tube 12 which is open only against the firing direction X. As a result, the wire 18 is only minimally acted upon by the hot powder gases and particles formed when the grenade 1 is fired.
  • the tube 2 of the grenade launcher is closed to protect against penetration of foreign particles at its front and rear ends with a lid 19 a, 19 b.
  • the rear lid 19a is connected to the grenade 1 via a holding device 20, which is arranged to hold the grenade 1 in a rear position in the tube 2 prior to firing.
  • the rear cover 19a does not represent a ballistic effective flow cross-section reduction of the launching tube 2, because it already shatters under the first action of the build-up gas pressure of the main charge 17 of the grenade 1.
  • the holding device 20 has a predetermined breaking point 21, at which the holding device 20 breaks during acceleration of the shell 1.
  • the grenade 1 has a firing chain which comprises a propellant charge igniter 22, a Matterzündladung 23, a base charge 15 and a main charge 17. This is just one of the possible embodiments of a detonating chain for the grenade according to the invention.
  • the ignition chain but can also have more or less elements.
  • the propellant charge igniter 22 ignites the overcharge charge 23 (for example, 500 mg of drilling potassium nitrate).
  • the propellant charge consists of two parts: As a basic charge, for example, 60 g Benits powder can be used, which is located in the starting pipe 13.
  • the overflow holes 16 of the starting pipe 13 are sealed with a brass foil.
  • the main charge 17 (for example, 300 g of Tecna powder) is ignited.
  • the gas pressure of the propellant charge 15 17 of the rear-side cover 19a is burst and the holding member 20 ruptures at its predetermined breaking point 21 from.
  • the gas pressure continues to build up, acts on the grenade bottom (ie on the rear side of the grenade body 10) and accelerates this.
  • a flow cross-section reduction device 12 is provided, which is not firmly connected to the launching tube 2, but is spaced from the latter by a connecting device 13 with the grenade base body 10 and connected in a fire-resistant manner. This ensures, on the one hand, that no axial forces are introduced into the grenade launcher when the grenade 1 is launched, and on the other hand, by the flow cross-section reduction device 12 for reducing the flow cross-section of the tube 2, which is arranged in relation to the grenade main body 10 in the opposite direction to the firing direction X, advantageously prevents too rapid outflow of gas pressure at launch of the grenade 1.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
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  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)

Description

Die Erfindung betrifft eine rohrverschießbare Granate gemäß dem Oberbegriff des Anspruchs 1 sowie eine Granatabschussvorrichtung mit einer solchen Granate.The invention relates to a rohrgehießbare grenade according to the preamble of claim 1 and a grenade launcher with such a grenade.

Eine derartige Granate ist aus der US 2 671 401 bekannt,Such a grenade is from the US 2 671 401 known,

Ein bekanntes Konzept zum Erreichen eines rückstossfreien Abschusses einer Granate aus einer Granatabschussvorrichtung liegt darin begründet, dass die Granatabschussvorrichtung aus einem beidseitig offenen Rohr besteht, welches keine Strömungsquerschnittsverengungen aufweist. Idealerweise ist dabei nicht nur der Betrag der Strömungsquerschnittsfläche über die gesamte Rohrlänge konstant, sondern auch die Form der Strömungsquerschnittsfläche. Beispielsweise weist die Strömungsquerschnittsfläche über die gesamte Rohrlänge eine Kreisscheibenform mit konstantem Radius auf. Dadurch wird gewährleistet, dass bei Abschuss der Granate keine axialen Kräfte auf das Rohr übertragen werden. Die Treibladungsgase der im Abschuss befindlichen Granate können das Rohr der Granatabschussvorrichtung ungehindert nach hinten verlassen. Der Impuls der nach vorne beschleunigten Granate entspricht betragsmäßig genau dem Impuls der das Rohr nach hinten verlassenden Treibladungsgase. Dieses Konzept hat zwar den Vorteil, dass mit einer relativ einfachen Bauweise der Granatabschussvorrichtung auf einfache Weise ein rückstoßfreier Abschuss einer rohrverschießbaren Granate erreicht werden kann, das Konzept hat aber gleichzeitig den Nachteil, dass der nach Zünden der Treibladung entstehende Gasdruck sehr schnell nach hinten durch das offene Rohrende abströmt. Die Vortriebswirkung auf die zu verschießende Granate ist daher nur gering.A known concept for achieving a recoil-free launch of a grenade from a grenade launcher is that the grenade launcher consists of a tube open on both sides which has no flow cross-sectional constrictions. Ideally, not only the amount of the flow cross-sectional area over the entire tube length is constant, but also the shape of the flow cross-sectional area. For example, the flow cross-sectional area over the entire tube length on a circular disk shape with a constant radius. This ensures that no axial forces are transmitted to the tube when the grenade is fired. The propellant gases of the grenade being launched can leave the tube of the grenade launcher unhindered to the rear. The momentum of the forward accelerated grenade corresponds exactly to the momentum of the propellant gases leaving the tube to the rear. Although this concept has the advantage that with a relatively simple design of the grenade launcher in a simple manner recoilless launching a tubular mortar can be achieved, but the concept has the disadvantage that the resulting after ignition of the propellant gas pressure very quickly backwards through the open pipe end flows out. The propulsive effect on the grenade to be fired is therefore only slight.

Es ist daher Aufgabe der vorliegenden Erfindung, eine rohrverschießbare Granate sowie eine zugehörige Granatabschussvorrichtung vorzuschlagen, bei welcher einerseits ein rückstoßfreier Abschuss der Granate gewährleistet ist, andererseits aber auch gleichzeitig eine große Vortriebswirkung auf die Granate erzielt wird.It is therefore an object of the present invention to propose a tubular grenade and an associated grenade launcher, in which on the one hand a recoilless launch of the grenade is ensured, on the other hand, but also a large propulsive action is achieved on the grenade.

Diese Aufgabe wird durch eine rohrverschießbare Granate nach Anspruch 1 und durch eine Granatabschussvorrichtung nach Anspruch 11 gelöst.This object is achieved by a tubular firing grenade according to claim 1 and by a grenade launcher according to claim 11.

Die Erfindung geht dabei von der Überlegung aus, dass durch eine Strömungsquerschnittsverengung im Abschussrohr grundsätzlich ein zu schnelles Abströmen des beim Abbrennen der Treibladung entstehenden Gasdrucks verhindert werden kann, wodurch letztlich die Vortriebswirkung auf den Granatenkörper verbessert werden kann. Verengt man jedoch die rückwärtige Öffnung des Abschussrohres zu diesem Zweck beispielsweise düsenförmig, so resultiert daraus neben der vorteilhaften Verstärkung der Vortriebswirkung auf den Granatenkörper auch eine nachteilige Einleitung einer axial nach hinten gerichteten Kraft in die Abschussvorrichtung.The invention is based on the idea that a flow cross-sectional constriction in the launch tube can in principle prevent too rapid outflow of the gas pressure arising when the propellant burns, which ultimately improves the propulsive effect on the shell body. However, narrowing the rear opening of the launch tube for this purpose, for example, nozzle-shaped, it results in addition to the advantageous reinforcement of the propulsive action on the grenade body also an adverse introduction of an axially rearward force in the launcher.

Erfindungsgemäß ist daher eine Strömungsquerschnittsverringerungseinrichtung vorgesehen, welche nicht mit dem Abschussrohr fest verbunden ist, sondern über eine Verbindungseinrichtung mit dem Granatengrundkörper von diesem beabstandet und abschussstabil verbunden ist. Dadurch ist einerseits gewährleistet, dass beim Abschuss der Granate keine axialen Kräfte in die Granatabschussvorrichtung eingeleitet werden, andererseits wird durch die Strömungsquerschnittsverringerungseinrichtung zur Verringerung des Strömungsquerschnitts des Rohres, welche in Bezug auf den Granatengrundkörper in entgegengesetzter Richtung zur Abschussrichtung angeordnet ist, in vorteilhafter Weise ein zu schnelles Abströmen des Gastrucks bei Abschuss der Granate verhindert.According to the invention, therefore, a flow cross-section reduction device is provided, which is not fixedly connected to the launching tube, but is spaced from it by a connecting device with the grenade base body and is connected in a fire-stable manner. This ensures, on the one hand, that no axial forces are introduced into the grenade launcher when the grenade is launched, and on the other hand, the flow cross-section reduction device advantageously reduces the flow cross-section of the tube, which is arranged in the opposite direction to the firing direction with respect to the grenade base body rapid escape of the gastruck prevented by launching the grenade.

Vorzugsweise weist der Granatengrundkörper eine zylindrische Form auf, deren Außendurchmesser im Wesentlichen dem Innendurchmesser des Abschussrohres entspricht. Dadurch kann zum einen das Ladungsvolumen der Granate maximiert werden, andererseits ist somit die Führung des Granatenkörpers im Abschussrohr optimiert.The grenade base body preferably has a cylindrical shape whose outer diameter substantially corresponds to the inner diameter of the launching tube. As a result, on the one hand the charge volume of the grenade can be maximized, on the other hand thus the guidance of the grenade body in the launching tube is optimized.

Dabei ist es insbesondere von Vorteil, dass der Granatengrundkörper an seiner Mantelfläche Dichtungsmittel aufweist, welche geeignet sind, Spalte zwischen der Mantelfläche des Granatengrundkörpers und der Innenfläche des Abschussrohres abzudichten. Dadurch kann verhindert werden, dass Treibladungsgase am Granatengrundkörper vorbei das Abschussrohr nach vorne verlassen, was zu einer Reduzierung der Vortriebswirkung auf die Granate führen würde.It is particularly advantageous that the grenade body has on its lateral surface sealing means which are suitable to seal gaps between the lateral surface of the grenade body and the inner surface of the launching tube. This can prevent propellant charge gases from leaving the launching tube at the front of the grenade body, which would lead to a reduction of the propulsion effect on the grenade.

Gemäß der Erfindung umfasst die Strömungsquerschnittsverringerungseinrichtung einen hohlzylinderförmigen Ring, welcher über einen oder mehrere Stege mit der Verbindungseinrichtung verbunden ist. Auf diese Weise kann eine leichtgewichtige und dennoch stabile Konstruktion der Strömungsquerschnittsverringerungseinrichtung gewährleistet werden.According to the invention, the flow cross-section reduction device comprises a hollow cylindrical ring, which is connected via one or more webs to the connecting device. In this way, a lightweight, yet stable construction of the flow cross-section reduction device can be ensured.

Vorzugsweise entspricht dabei der Außendurchmesser des Rings zumindest über einen Teil der Höhe des Hohlzylinders dem Außendurchmesser des zylinderförmigen Granatengrundkörpers. Dadurch wird die Führung der rohrverschießbaren Granate verbessert und ein Verkanten der Granate im Abschussrohr vermieden.Preferably, the outer diameter of the ring at least over a portion of the height of the hollow cylinder corresponds to the outer diameter of the cylindrical grenade body. This improves the guidance of the tubular grenade and avoids jamming of the grenade in the launching tube.

Weiterhin ist es von Vorteil, wenn die Kanten der Stege und/oder des Rings an der dem Granatengrundkörper zugewandten Seite angeschrägt sind. Dadurch wird eine aerodynamisch günstige Anströmung der Stege und/oder des Rings durch die Treibladungsgase erzielt.Furthermore, it is advantageous if the edges of the webs and / or the ring are beveled on the side facing the grenade body. As a result, an aerodynamically favorable flow of the webs and / or the ring is achieved by the propellant charge gases.

Ferner ist es von Vorteil, wenn die Wandungen der Stege und/oder des Rings derart angeformt sind, dass die Hohlräume zwischen ihnen Düsenform aufweisen. Damit kann eine verbesserte Schubwirkung auf die Granate erreicht werden. Eine besonders gute Schubwirkung wird erzielt, wenn die Düsenform die einer Laval-Düse ist.Furthermore, it is advantageous if the walls of the webs and / or the ring are formed such that the cavities between them have a nozzle shape. Thus, an improved thrust on the grenade can be achieved. A particularly good thrust effect is achieved when the nozzle shape is that of a Laval nozzle.

Vorzugsweise weist die die Strömungsquerschnittsverringerungseinrichtung die Form eines Ringleitwerks auf. Dies hat den Vorteil, dass die Granate nach Verlassen des Rohres flugstabilisiert wird.The flow cross-section reduction device preferably has the shape of a ring guide. This has the advantage that the grenade is flight stabilized after leaving the tube.

Gemäß einer bevorzugten Ausführungsform der Erfindung umfasst die Verbindungseinrichtung ein sich in Verlängerung zur Zylinderlängsachse des Granatengrundkörpers erstreckendes Startrohr. Dieses Startrohr beinhaltet eine Grundladung. Die Grundladung kann dabei den mittleren Teil einer Zündkette darstellen, welche Überzündladung, Grundladung und Hauptladung umfasst. Vorzugsweise weist das Startrohr radiale Bohrungen auf, welche ein Überzünden von der gezündeten Grundladung auf eine ringförmig um das Startrohr und zwischen Granatengrundkörper und Strömungsquerschnittsverringerungseinrichtung anordenbare Hauptladung ermöglichen. Diese Überströmbohrungen des Startrohrs können mit einer Messingfolie abgedichtet sein. Nach Erreichen des Berstdruckes der Messingfolie wird durch die aus den Überströmbohrungen ausströmenden Verbrennungsgase der Grundladung die Hauptladung angezündet.According to a preferred embodiment of the invention, the connecting device comprises an extension tube extending in extension to the cylinder longitudinal axis of the grenade body. This launch tube includes a base charge. The base charge may represent the middle part of a detonating chain, which includes Überzündladung, base charge and main charge. Preferably, the starting pipe has radial bores which allow over-ignition of the ignited basic charge to a main charge which can be arranged annularly around the starting pipe and between the grenade base body and the flow cross-section reduction means. These overflow holes of the starting pipe can be sealed with a brass foil. After reaching the bursting pressure of the brass foil, the main charge is ignited by the combustion gases flowing out of the overflow holes of the base charge.

Gemäß der Erfindung ist die Strömungsquerschnittsverringerungseinrichtung Träger eines drahtgebundenen, während des Abschusses der Granate abwickelbaren Datenlinks, welcher die Granate zumindest bis zum Verlassen des Abschussrohres oder auch in der Anfangsflugphase der Granate nach Verlassen des Abschussrohres mit einem Feuerleitrechner verbindet. Dabei ist der abwickelbare Draht des Datenlinks derart an der Strömungsquerschnittsverringerungseinrichtung angeordnet, dass der Draht möglichst wenig von den bei Abschuss der Granate entstehenden heißen Pulvergasen und -partikeln beaufschlagt wird. Dadurch kann in vorteilhafter Weise gewährleistet werden, dass der Draht des Datenlinks bei Abschuss der Granate nicht reißt. Dabei ist der Draht in einem nur entgegen Abschussrichtung offenen, hohlzylinderförmigen Spalt zwischen Außendurchmesser des Rings und Innenfläche des Abschussrohres spulenförmig um den Ring gewickelte. Dadurch ist der Draht besonders gut von den bei Abschuss der Granate entstehenden heißen Pulvergasen geschützt und gleichzeitig ist eine leichte Abwickelbarkeit des Drahtes gewährleistet.According to the invention, the flow cross-section reduction device carries a wired data link which can be developed during the firing of the grenade and connects the grenade to a fire control computer at least until it leaves the launching tube or during the initial flight phase of the grenade after leaving the launching tube. In this case, the unwindable wire of the data link is arranged on the flow cross-section reduction device in such a way that the wire is subjected as little as possible to the hot powder gases and particles formed when the grenade is fired. As a result, it can be ensured in an advantageous manner that the wire of the data link does not tear when the grenade is launched. In this case, the wire is wound in a coil shape around the ring in a hollow cylinder-shaped gap between outer diameter of the ring and inner surface of the launching tube that is open only against the firing direction. As a result, the wire is particularly well protected by the hot powder gases resulting from the launch of the grenade and at the same time ensures easy unwindability of the wire.

Die vorliegende Erfindung umfasst ferner auch eine Granatabschussvorrichtung mit einer Granate, wie sie voranstehend beschrieben wurde. Dabei weist die Granatabschussvorrichtung ein beidseitig offenes Rohr ohne Strömungsquerschnittsverengungen auf.The present invention also includes a grenade launcher having a grenade as described above. In this case, the grenade launcher has a tube open on both sides without flow cross-sectional constrictions.

Vorzugsweise ist das Rohr der Granatabschussvorrichtung an seinem vorderen und/oder hinteren Ende vor dem Abschuss der Granate mit einem Deckel verschlossen. Dadurch kann verhindert werden, dass Fremdkörper in das Rohr der Granatabschussvorrichtung gelangen. Vorzugsweise ist der hintere Deckel mit der Granate über eine Halteeinrichtung verbunden, welche eingerichtet ist, die Granate vor dem Abschuss in einer hinteren Position im Rohr zu halten. Dadurch kann verhindert werden, dass die Granate vor dem Abschuss im Rohr hin und her rutscht. Insbesondere beim Transport der Granatabschussvorrichtung können somit Beschädigungen der in ihr befindlichen Granate vermieden werden.Preferably, the tube of the grenade launcher is closed at its front and / or rear end before the launch of the grenade with a lid. This can prevent foreign bodies from getting into the tube of the grenade launcher. Preferably, the rear lid is connected to the grenade via a holding device which is arranged to hold the grenade in a rear position in the tube before launching. This will prevent the grenade from slipping back and forth in the tube before launching. In particular, during transport of the grenade launcher thus damage the grenade located in it can be avoided.

Vorzugsweise ist der hintere Deckel eingerichtet, unter Einwirkung des sich aufbauenden Gasdrucks der Hauptladung der Granate zu bersten, um das hintere Ende des Rohres freizugeben. Auf diese Weise kann gewährleistet werden, dass die Schutzwirkung des Deckels solange wie möglich aufrechterhalten bleibt.Preferably, the rear cover is configured to burst under the action of the build-up gas pressure of the main charge of the shell to release the rear end of the tube. In this way it can be ensured that the protective effect of the lid is maintained as long as possible.

Dabei ist es insbesondere von Vorteil, wenn die Halteeinrichtung, über welche der hintere Deckel mit der Granate verbunden ist, eine Sollbruchstelle aufweist, an welcher die Halteeinrichtung bei Beschleunigung der Granate bricht. Auf diese Weise kann die Einleitung axialer Kräfte in die Granatabschussvorrichtung bei Abschuss der Granate auf ein Minimum reduziert werden.It is particularly advantageous if the holding device, via which the rear cover is connected to the shell, has a predetermined breaking point, at which the holding device breaks during acceleration of the shell. In this way, the initiation of axial forces into the grenade launcher upon launch of the grenade can be minimized.

Weitere vorteilhafte Ausführungsformen und Verbesserungen der Erfindung ergeben sich aus nachstehender Beschreibung von bevorzugten Realisierungsbeispielen der Erfindung. Es wird darauf hingewiesen, dass die Erfindung auch weitere Ausführungsformen umfasst, die sich aus einer Kombination von Merkmalen ergeben, die getrennt in den Patentansprüchen und/oder in der Beschreibung und den Figuren aufgeführt sind.Further advantageous embodiments and improvements of the invention will become apparent from the following description of preferred implementation examples of the invention. It should be noted that the invention also encompasses further embodiments that result from a combination of features that are listed separately in the patent claims and / or in the description and the figures.

Nachstehend wird die Erfindung anhand ihrer vorteilhaften Ausführungsformen unter Bezugnahme auf die Zeichnungen näher erläutert.The invention will be explained in more detail below on the basis of its advantageous embodiments with reference to the drawings.

In den Zeichnungen bezeichnen die gleichen oder ähnlichen Bezugszeichen gleiche oder ähnliche Teile. In den Zeichnungen zeigen:

Figuren 1a und 1b
perspektivische Darstellungen einer bevorzugten Ausführungsform der erfindungsgemäßen rohrverschießbaren Granate,
Figur 2a
eine Schnittzeichnung durch eine bevorzugte Ausführungsform einer erfindungsgemäßen Granatabschussvorrichtung mit einer erfindungsgemäßen Granate, und
Figur 2b
eine vergrößerte Darstellung des rechten (hinteren) Teils der Schnittzeichnung aus Figur 2a.
In the drawings, the same or similar reference numerals designate the same or similar parts. In the drawings show:
FIGS. 1a and 1b
perspective views of a preferred embodiment of the tube-fireable grenade according to the invention,
FIG. 2a
a sectional view through a preferred embodiment of a grenade launcher according to the invention with a grenade according to the invention, and
FIG. 2b
an enlarged view of the right (rear) part of the sectional drawing FIG. 2a ,

Unter Bezugnahme auf Figuren 1 a und 1 b wird nun prinzipiell der erfindungsgemäße Gegenstand erläutert.With reference to FIGS. 1 a and 1 b, the object according to the invention will now be explained in principle.

Figuren 1 a und 1 b zeigen eine rohrverschießbare Granate 1, welche einen Granatengrundkörper 10 umfasst. Die Granate umfasst eine Strömungsquerschnittsverringerungseinrichtung 12, welche in Bezug auf den Granatengrundkörper 10 in entgegengesetzter Richtung zur Abschussrichtung X der Granate 1 angeordnet ist. Die Strömungsquerschnittsverringerungseinrichtung 12 ist über eine Verbindungseinrichtung 13 mit dem Granatengrundkörper 10 vom Granatengrundkörper 10 beabstandet und abschussstabil verbunden. Diese Granate 1 kann rückstossfrei aus einem beidseitig offenen Rohr 2 abgeschossen werden. Die erfindungsgemäße Ausgestaltung der Strömungsquerschnittsverringerungseinrichtung 12 gewährleistet, dass beim Abschuss der Granate 1 keine axialen Kräfte in die Granatabschussvorrichtung eingeleitet werden. Gleichzeitig wird dadurch gewährleistet, dass der Strömungsquerschnitt des Abschussrohres 2 verringert wird, wodurch ein zu schnelles Abströmen des Gasdrucks bei Abschuss der Granate 1 verhindert wird. FIGS. 1 a and 1 b show a tubular shell grenade 1, which comprises a shell body 10. The grenade comprises a flow cross-section reduction device 12, which in relation to the grenade main body 10 in the opposite direction to the firing direction X of Grenade 1 is arranged. The flow cross-section reduction device 12 is spaced apart from the grenade base body 10 via a connecting device 13 with the grenade main body 10 and connected in a stable manner to the launch. This grenade 1 can recoilless be fired from a tube 2 open on both sides. The inventive design of the flow cross-section reduction device 12 ensures that no axial forces are introduced into the grenade launcher when the grenade 1 is launched. At the same time, this ensures that the flow cross-section of the launching tube 2 is reduced, as a result of which a too rapid outflow of the gas pressure when the shell 1 is fired is prevented.

Die nachfolgend beschriebenen Merkmale stellen vorteilhafte Ausgestaltungen des voranstehend beschriebenen Erfindungsprinzips dar.The features described below represent advantageous embodiments of the invention described above principle.

So weist der in Figuren 1a und 1b dargestellte Granatengrundkörper 10 eine zylindrische Form auf. Der Außendurchmesser dieser zylindrischen Form entspricht vorzugsweise im Wesentlichen dem Innendurchmesser des Abschussrohres 2, aus welchem die Granate 1 verschossen wird. Der Granatengrundkörper 10 weist an seiner Mantelfläche zumindest einen Dichtungsring 14 auf. Mittels dieser Dichtungsringe können Spalte zwischen der Mantelfläche des Granatengrundkörpers 10 und der Innenfläche des Abschussrohres 2 abgedichtet werden. Die Strömungsquerschnittsverringerungseinrichtung 12 umfasst einen hohlzylinderförmigen Ring 12a. Dieser Ring 12a ist über einen oder mehrere Stege 12b mit der Verbindungseinrichtung 13 verbunden. Der Außendurchmesser des Rings 12a entspricht auf der dem Granatengrundkörper 10 zugewandten Seite dem Außendurchmesser des zylinderförmigen Granatengrundkörpers 10. Dahinter verjüngt sich der Ring 12a zu einem hohlzylinderförmigen Ring mit etwas kleinerem Radius. Die Kanten der Stege 12b und des Rings 12a sind an der dem Granatengrundkörper 10 zugewandten Seite angeschrägt. Die Wandungen der Stege 12b und des Rings 12a sind derart angeformt, dass die Hohlräume zwischen ihnen eine Düsenform aufweisen. Die Strömungsquerschnittsverringerungseinrichtung 12 weist die Form eines Ringleitwerks auf. Die Verbindungseinrichtung 13 umfasst ein sich in Verlängerung zur Zylinderlängsachse des Granatengrundkörpers 10 erstreckendes Rohr. Dieses Rohr 13 beinhaltet eine Grundladung 15. Das Rohr 13 weist radiale Bohrungen 16 auf, welche ein Überzünden von der gezündeten Grundladung 15 auf eine ringförmig um das Startrohr und zwischen Granatengrundkörper 10 und Strömungsquerschnittsverringerungseinrichtung 12 anordenbare Hauptladung 17 ermöglichen. Diese Hauptladung 17 kann eine oder mehrere Lochscheiben aus Treibladungsmaterial umfassen, durch welche das Rohr 13 hindurchragt.Thus, the in FIGS. 1a and 1b Granatgrundkörper 10 shown a cylindrical shape. The outer diameter of this cylindrical shape preferably corresponds substantially to the inner diameter of the launching tube 2, from which the shell 1 is fired. The shell body 10 has at least one sealing ring 14 on its lateral surface. By means of these sealing rings gaps between the lateral surface of the grenade body 10 and the inner surface of the launching tube 2 can be sealed. The flow cross-section reduction device 12 comprises a hollow cylindrical ring 12a. This ring 12a is connected to the connecting device 13 via one or more webs 12b. The outer diameter of the ring 12a corresponds to the grenade base body 10 side facing the outer diameter of the cylindrical grenade body 10. Behind the ring 12a tapers to a hollow cylindrical ring with a slightly smaller radius. The edges of the webs 12b and the ring 12a are beveled on the grenade base body 10 facing side. The walls of the webs 12b and 12a of the ring are formed such that the cavities between them have a nozzle shape. The flow cross-section reduction device 12 has the shape of a ring guide. The connecting device 13 comprises a tube extending in extension to the cylinder longitudinal axis of the grenade main body 10. This tube 13 contains a basic charge 15. The tube 13 has radial bores 16, which can be ignited by the ignited base charge 15 onto a main charge 17 that can be arranged annularly around the starting tube and between the grenade base body 10 and the flow cross-section reduction device 12 enable. This main charge 17 may include one or more perforated discs of propellant material through which the tube 13 protrudes.

Unter Bezugnahme auf Figuren 2a und 2b wird nachfolgend eine bevorzugte Ausführungsform einer erfindungsgemäßen Granatabschussvorrichtung sowie eine bevorzugte Ausführungsform der Strömungsquerschnittsverringerungseinrichtung 12 erläutert.With reference to FIGS. 2a and 2 B Below, a preferred embodiment of a grenade launcher according to the invention and a preferred embodiment of the flow cross-section reduction device 12 will be explained.

Die Granatabschussvorrichtung weist ein beidseitig offenes Rohr 2 ohne Strömungsquerschnittsverengungen auf. In dem Rohr ist eine Granate 1 gelagert, wie sie voranstehend und nachfolgend beschrieben ist.The grenade launcher has a tube 2 open on both sides without flow cross-sectional constrictions. In the tube, a grenade 1 is mounted, as described above and below.

Die Strömungsquerschnittsverringerungseinrichtung 12 ist als Träger eines drahtgebundenen, während des Abschusses der Granate 1 abwickelbaren Datenlinks 18 ausgebildet. Dieser Datenlink 18 verbindet die Granate 1 zumindest bis zum Verlassen des Abschussrohres 2 oder auch in der Anfangsflugphase der Granate 1 nach Verlassen des Abschussrohres 2 mit einem Feuerleitrechner (nicht dargestellt). Der Draht 18 ist in einem nur entgegen Abschussrichtung X offenen, hohlzylinderförmigen Spalt zwischen Außendurchmesser des Rings 12a und Innenfläche des Abschussrohres 12 spulenförmig um den Ring 12a gewickelt. Dadurch wird der Draht 18 nur minimal von den bei Abschuss der Granate 1 entstehenden heißen Pulvergasen und -partikeln beaufschlagt.The flow cross-section reduction device 12 is embodied as a carrier of a wired data link 18 that can be developed during the firing of the grenade 1. This data link 18 connects the grenade 1 at least until leaving the launching tube 2 or in the initial flight phase of the grenade 1 after leaving the launching tube 2 with a Feuerleitrechner (not shown). The wire 18 is wound around the ring 12a in a coil shape around the ring 12a in a hollow cylinder-shaped gap between outer diameter of the ring 12a and inner surface of the launch tube 12 which is open only against the firing direction X. As a result, the wire 18 is only minimally acted upon by the hot powder gases and particles formed when the grenade 1 is fired.

Das Rohr 2 der Granatabschussvorrichtung ist zum Schutz vor Eindringen von Fremdpartikeln an seinem vorderen und hinteren Ende mit einem Deckel 19a, 19b verschlossen. Der hintere Deckel 19a ist mit der Granate 1 über eine Halteeinrichtung 20 verbunden, welche eingerichtet ist, die Granate 1 vor dem Abschuss in einer hinteren Position im Rohr 2 zu halten. Der hintere Deckel 19a stellt keine ballistische wirksame Strömungsquerschnittsverringerung des Abschussrohres 2 dar, denn er zerbirst bereits unter der ersten Einwirkung des sich aufbauenden Gasdrucks der Hauptladung 17 der Granate 1. Dadurch wird das hintere Ende des Rohres 2 sofort freigegeben, ohne dass axiale Kräfte in die Granatabschussvorrichtung eingeleitet werden. Die Halteeinrichtung 20 weist eine Sollbruchstelle 21 auf, an welcher die Halteeinrichtung 20 bei Beschleunigung der Granate 1 bricht. Die Granate 1 weist eine Zündkette auf, welche einen Treibladungsanzünder 22, eine Überzündladung 23, eine Grundladung 15 und eine Hauptladung 17 umfasst. Dies ist nur eine der möglichen Ausgestaltungen einer Zündkette für die erfindungsgemäße Granate. Die Zündkette kann aber auch mehr oder weniger Elemente aufweisen. Der Treibladungsanzünder 22 zündet die Überzündladung 23 (beispielsweise 500 mg Bohr-Kaliumnitrat) an. Die Treibladung besteht aus zwei Teilen: Als Grundladung kann beispielsweise 60 g Benits-Pulver verwendet werden, welches sich im Startrohr 13 befindet. Die Überströmbohrungen 16 des Startrohrs 13 sind mit einer Messingfolie abgedichtet. Nach Erreichen des Berstdruckes der Messingfolie wird schließlich die Hauptladung 17 (beispielsweise 300 g Tecna-Pulver) angezündet. Durch den Gasdruck der Treibladung 15, 17 wird der heckseitige Deckel 19a geborsten und das Halteelement 20 reißt an seiner Sollbruchstelle 21 ab. In Folge der Querschnittsverengung durch die Leitwerksquerschnittsfläche baut sich der Gasdruck weiter auf, wirkt auf den Granatenboden (also auf die Hinterseite des Granatengrundkörpers 10) und beschleunigt diesen.The tube 2 of the grenade launcher is closed to protect against penetration of foreign particles at its front and rear ends with a lid 19 a, 19 b. The rear lid 19a is connected to the grenade 1 via a holding device 20, which is arranged to hold the grenade 1 in a rear position in the tube 2 prior to firing. The rear cover 19a does not represent a ballistic effective flow cross-section reduction of the launching tube 2, because it already shatters under the first action of the build-up gas pressure of the main charge 17 of the grenade 1. Thus, the rear end of the tube 2 is released immediately without axial forces in the Granatabschussvorrichtung be initiated. The holding device 20 has a predetermined breaking point 21, at which the holding device 20 breaks during acceleration of the shell 1. The grenade 1 has a firing chain which comprises a propellant charge igniter 22, a Überzündladung 23, a base charge 15 and a main charge 17. This is just one of the possible embodiments of a detonating chain for the grenade according to the invention. The ignition chain but can also have more or less elements. The propellant charge igniter 22 ignites the overcharge charge 23 (for example, 500 mg of drilling potassium nitrate). The propellant charge consists of two parts: As a basic charge, for example, 60 g Benits powder can be used, which is located in the starting pipe 13. The overflow holes 16 of the starting pipe 13 are sealed with a brass foil. After reaching the bursting pressure of the brass foil, finally, the main charge 17 (for example, 300 g of Tecna powder) is ignited. By the gas pressure of the propellant charge 15, 17 of the rear-side cover 19a is burst and the holding member 20 ruptures at its predetermined breaking point 21 from. As a result of the cross-sectional constriction through the tail cross section surface, the gas pressure continues to build up, acts on the grenade bottom (ie on the rear side of the grenade body 10) and accelerates this.

Erfindungsgemäß ist eine Strömungsquerschnittsverringerungseinrichtung 12 vorgesehen, welche nicht mit dem Abschussrohr 2 fest verbunden ist, sondern über eine Verbindungseinrichtung 13 mit dem Granatengrundkörper 10 von diesem beabstandet und abschussstabil verbunden ist. Dadurch ist einerseits gewährleistet, dass beim Abschuss der Granate 1 keine axialen Kräfte in die Granatabschussvorrichtung eingeleitet werden, andererseits wird durch die Strömungsquerschnittsverringerungseinrichtung 12 zur Verringerung des Strömungsquerschnitts des Rohres 2, welche in Bezug auf den Granatengrundkörper 10 in entgegengesetzter Richtung zur Abschussrichtung X angeordnet ist, in vorteilhafter Weise ein zu schnelles Abströmen des Gasdrucks bei Abschuss der Granate 1 verhindert.According to the invention, a flow cross-section reduction device 12 is provided, which is not firmly connected to the launching tube 2, but is spaced from the latter by a connecting device 13 with the grenade base body 10 and connected in a fire-resistant manner. This ensures, on the one hand, that no axial forces are introduced into the grenade launcher when the grenade 1 is launched, and on the other hand, by the flow cross-section reduction device 12 for reducing the flow cross-section of the tube 2, which is arranged in relation to the grenade main body 10 in the opposite direction to the firing direction X, advantageously prevents too rapid outflow of gas pressure at launch of the grenade 1.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Granategrenade
22
Abschussrohrlaunching tube
1010
GranatengrundkörperGrenades body
1111
Sprengladungexplosive charge
1212
StrömungsquerschnittsverringerungseinrichtungFlow cross-section reducer
12a12a
Hohlzylinderförmiger RingHollow cylindrical ring
12b12b
StegeStege
1313
Verbindungseinrichtungconnecting device
1414
Dichtungsmittelsealant
1515
Grundladungbasic charge
1616
Radiale Bohrungen (in 13)Radial holes (in 13)
1717
Hauptladungmain charge
1818
Draht/DatenlinkWire / data link
19a19a
Hinterer DeckelRear lid
19b19b
Vorderer DeckelFront lid
2020
Halteeinrichtungholder
2121
Sollbruchstelle (in 20)Breaking point (in 20)
2222
Treibladungsanzündercharge igniter
2323
ÜberzündladungÜberzündladung
XX
Abschussrichtungfiring direction

Claims (11)

  1. Shell (1), which can be fired from a barrel, for recoilless firing from a barrel (2) which is open at both ends without any flow cross-section constrictions, comprising a shell base body (10) which surrounds at least one explosive charge (11), and
    a flow cross-section reduction device (12) for reducing the flow cross-section of the barrel (2), which device (12) is arranged in the opposite direction to the firing direction (X) with respect to the shell base body (10),
    wherein the flow cross-section reduction device (12) is connected to the shell base body (10), at a distance from it and to make it stable during firing, via a connecting device (13),
    and wherein the flow cross-section reduction device (12) comprises a hollow-cylindrical ring (12a), which is connected to the connecting device (13) via one or more webs (12b),
    characterized
    in that the flow cross-section reduction device (12) is a support for a wire-bound data link (18), which can be unwound while the shell is being fired and connects the shell (1) to a firing control computer at least until it leaves the firing barrel (2) or else in the initial flight phase of the shell (1) after leaving the firing barrel (2), wherein the wire which can be unwound for the data link (18) is arranged on the flow cross-section reduction device (12) such that the wire (18) is affected as little as possible by the hot powder gases and particles which are created when the shell (1) is fired,
    wherein the wire (18) is wound in the form of a coil around the ring (12a) in a hollow-cylindrical gap, which is open only in the opposite direction to the firing direction (X), between the external diameter of the ring (12a) and the inner surface of the firing barrel (2).
  2. Shell according to Claim 1,
    wherein the shell base body (10) has a cylindrical shape, the external diameter of which corresponds essentially to the internal diameter of the firing barrel (2).
  3. Shell according to Claim 2,
    wherein the shell base body (10) has on its lateral surface sealing means (14) that are suitable for sealing gaps between the lateral surface of the shell base body (10) and the inner surface of the firing barrel (2).
  4. Shell according to Claim 3,
    wherein the external diameter of the ring (12a) corresponds to the external diameter of the cylindrical shell base body (10) at least over part of the height of the hollow cylinder.
  5. Shell according to Claim 3 or 4,
    wherein the edges of the webs (12b) and/or of the ring (12a) are bevelled on the side facing the shell base body (10).
  6. Shell according to one of Claims 3 to 5,
    wherein the walls of the webs (12b) and/or of the ring (12a) are shaped such that the cavities between them are in the form of nozzles.
  7. Shell according to Claim 6,
    wherein the nozzle shape is a de Laval nozzle.
  8. Shell according to one of Claims 1 to 7,
    wherein the flow cross-section reduction device (12) is in the form of an annular fin structure.
  9. Shell according to one of Claims 1 to 8,
    wherein the connecting device (13) comprises a launch barrel, which extends as an elongation of the cylinder longitudinal axis of the shell base body (10) and contains a basic charge (15).
  10. Shell according to Claim 9,
    wherein the launch tube has radial holes (16), which allow the ignited basic charge (15) to flash over to a main charge (17), which can be arranged in an annular shape around the launch barrel and between the shell base body (10) and the flow cross-section reduction device (12).
  11. Shell firing device with a shell (1) according to one of Claims 1 to 10,
    wherein the shell firing device has a barrel (2) which is open at both ends without any flow cross-section constrictions.
EP10015602.5A 2009-12-22 2010-12-14 Grenade and grenade launching device Active EP2339285B8 (en)

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Application Number Priority Date Filing Date Title
DE102009060658A DE102009060658B4 (en) 2009-12-22 2009-12-22 Grenade and grenade launcher

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EP2339285A3 EP2339285A3 (en) 2014-05-07
EP2339285B1 true EP2339285B1 (en) 2017-03-29
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US8967046B2 (en) * 2012-11-30 2015-03-03 Alliant Techsystems Inc. Gas generators, launch tubes including gas generators and related systems and methods
TR201907451T4 (en) * 2013-11-27 2019-06-21 Security Devices Int Inc One bullet.

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IL210095A (en) 2013-12-31
US20110162247A1 (en) 2011-07-07
DE102009060658B4 (en) 2012-11-15
EP2339285A3 (en) 2014-05-07
EP2339285B8 (en) 2017-05-31
US9488422B2 (en) 2016-11-08
EP2339285A2 (en) 2011-06-29
DE102009060658A1 (en) 2011-06-30
IL210095A0 (en) 2011-03-31

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