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EP2339285B1 - Grenade et dispositif de lancement de grenade - Google Patents

Grenade et dispositif de lancement de grenade 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
Authority
EP
European Patent Office
Prior art keywords
shell
grenade
flow cross
firing
base body
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP10015602.5A
Other languages
German (de)
English (en)
Other versions
EP2339285A2 (fr
EP2339285A3 (fr
EP2339285B8 (fr
Inventor
Helmut Hammer
Axel Pfersmann
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.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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 Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP2339285A2 publication Critical patent/EP2339285A2/fr
Publication of EP2339285A3 publication Critical patent/EP2339285A3/fr
Publication of EP2339285B1 publication Critical patent/EP2339285B1/fr
Application granted granted Critical
Publication of EP2339285B8 publication Critical patent/EP2339285B8/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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)
  • Toys (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)

Claims (11)

  1. Grenade pouvant être lancée par tube (1) permettant un lancement sans recul à partir d'un tube ouvert des deux côtés (2) sans étranglements de la section transversale d'écoulement, comprenant un corps de base de grenade (10), qui entoure au moins une charge explosive (11), et
    un dispositif de réduction de la section transversale d'écoulement (12) permettant de réduire la section transversale d'écoulement du tube (2), qui est disposé dans une direction opposée à la direction de lancement (X) par rapport au corps de base de grenade (10),
    dans laquelle le dispositif de réduction de la section transversale d'écoulement (12) est relié par l'intermédiaire d'un dispositif de liaison (13) au corps de base de grenade (10) de manière espacée de celui-ci et de manière stable au lancement,
    et dans laquelle le dispositif de réduction de la section transversale d'écoulement (12) comprend un anneau de forme cylindrique creuse (12a), qui est relié au dispositif de liaison (13) par l'intermédiaire d'une ou de plusieurs barres (12b),
    caractérisée en ce que le dispositif de réduction de la section transversale d'écoulement (12) est le support d'une liaison de données (18) filaire pouvant être déroulée pendant le lancement de la grenade, qui relie la grenade (1), au moins jusqu'à sa sortie du tube de lancement (2) ou également au cours de la phase de vol de la grenade (1) après sa sortie du tube de lancement (2), à un calculateur de conduite de tir,
    dans laquelle le fil pouvant être déroulé de la liaison de données (18) est disposé sur le dispositif de réduction de la section transversale d'écoulement (12) de manière à ce que le fil (18) soit le moins possible exposé, lors du lancement de la grenade (1), aux gaz de poudre et aux particules à haute température produits, dans laquelle le fil (18) est enroulé en forme de bobine autour de l'anneau (12a) dans un interstice de forme cylindrique creuse uniquement ouvert en sens opposé à la direction de lancement (X), entre le diamètre extérieur de l'anneau (12a) et la surface interne du tube de lancement (2).
  2. Grenade selon la revendication 1,
    dans laquelle le corps de base de grenade (10) présente une forme cylindrique, dont le diamètre extérieur correspond sensiblement au diamètre intérieur du tube de lancement (2).
  3. Grenade selon la revendication 2, dans laquelle le corps de base de grenade (10) comporte sur sa surface enveloppante des moyens d'étanchéité (14) qui sont appropriés pour étanchéifier des interstices entre la surface enveloppante du corps de base de grenade (10) et la surface interne du tube de lancement (2).
  4. Grenade selon la revendication 3, dans laquelle le diamètre extérieur de l'anneau (12a) correspond au moins sur une partie de la hauteur du cylindre creux au diamètre extérieur du corps de base de grenade cylindrique (10).
  5. Grenade selon la revendication 3 ou 4,
    dans laquelle les arêtes des barres (12b) et/ou de l'anneau (12a) sont biseautées du côté qui est tourné vers le corps de base de grenade (10).
  6. Grenade selon l'une quelconque des revendications 3 à 5,
    dans laquelle les parois des barres (12b) et/ou de l'anneau (12a) sont formées de manière à ce que les cavités définies entre elles présentent une forme de buse.
  7. Grenade selon la revendication 6,
    dans laquelle la forme de buse est une buse Laval.
  8. Grenade selon l'une quelconque des revendications 1 à 7,
    dans laquelle le dispositif de réduction de la section transversale d'écoulement (12) présente la forme d'un empennage annulaire.
  9. Grenade selon l'une quelconque des revendications 1 à 8,
    dans laquelle le dispositif de liaison (13) comprend un tube lanceur, s'étendant dans le prolongement de l'axe longitudinal de cylindre du corps de base de grenade (10), qui contient une charge de base (15).
  10. Grenade selon la revendication 9,
    dans laquelle le tube lanceur comporte des alésages radiaux (16) qui permettent un transfert d'allumage de de la charge de base allumée (15) à une charge principale (17) annulaire pouvant être disposée autour du tube lanceur et entre le corps de base de grenade (10) et le dispositif de réduction de la section transversale d'écoulement (12).
  11. Dispositif de tir de grenade comportant une grenade (1) selon l'une quelconque des revendications 1 à 10,
    dans lequel le dispositif de tir de grenade comporte un tube (2) ouvert des deux côtés sans étranglements de la section transversale d'écoulement.
EP10015602.5A 2009-12-22 2010-12-14 Grenade et dispositif de lancement de grenade Active EP2339285B8 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009060658A DE102009060658B4 (de) 2009-12-22 2009-12-22 Granate und Granatabschussvorrichtung

Publications (4)

Publication Number Publication Date
EP2339285A2 EP2339285A2 (fr) 2011-06-29
EP2339285A3 EP2339285A3 (fr) 2014-05-07
EP2339285B1 true EP2339285B1 (fr) 2017-03-29
EP2339285B8 EP2339285B8 (fr) 2017-05-31

Family

ID=43447739

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10015602.5A Active EP2339285B8 (fr) 2009-12-22 2010-12-14 Grenade et dispositif de lancement de grenade

Country Status (4)

Country Link
US (1) US9488422B2 (fr)
EP (1) EP2339285B8 (fr)
DE (1) DE102009060658B4 (fr)
IL (1) IL210095A (fr)

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US8065961B1 (en) * 2007-09-18 2011-11-29 Kimball Rustin Scarr Less lethal ammunition
DE102009011447B9 (de) * 2009-03-03 2012-08-16 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Zünden eines Gefechtskopfs einer Granate und Fahrzeug
WO2011038369A1 (fr) * 2009-09-25 2011-03-31 John William Hunter Véhicule pour le lancement à partir d'un canon à gaz
US8205829B2 (en) * 2010-03-03 2012-06-26 Raytheon Company Submersible transport and launch canister and methods for the use thereof
US9021960B1 (en) * 2013-06-06 2015-05-05 The United States Of America As Represented By The Secretary Of The Army Isolated coaxial high-pressure feed-through fitting

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

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