EP1674817A1 - Cartouche - Google Patents

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Publication number
EP1674817A1
EP1674817A1 EP05027946A EP05027946A EP1674817A1 EP 1674817 A1 EP1674817 A1 EP 1674817A1 EP 05027946 A EP05027946 A EP 05027946A EP 05027946 A EP05027946 A EP 05027946A EP 1674817 A1 EP1674817 A1 EP 1674817A1
Authority
EP
European Patent Office
Prior art keywords
propellant charge
tail
sleeve
cartridge
casing
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.)
Granted
Application number
EP05027946A
Other languages
German (de)
English (en)
Other versions
EP1674817B1 (fr
Inventor
Thomas Heitmann
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 Waffe Munition GmbH
Original Assignee
Rheinmetall Waffe Munition 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 Waffe Munition GmbH filed Critical Rheinmetall Waffe Munition GmbH
Publication of EP1674817A1 publication Critical patent/EP1674817A1/fr
Application granted granted Critical
Publication of EP1674817B1 publication Critical patent/EP1674817B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F42B5/18—Caseless ammunition; Cartridges having combustible cases
    • F42B5/181—Caseless ammunition; Cartridges having combustible cases consisting of a combustible casing wall and a metal base; Connectors therefor
    • 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
    • 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 cartridge with a fixed to the bottom of the case combustible propellant charge sleeve and a stabilizer stabilized projectile, the tail of which projects into the filled with a propellant powder propellant, and wherein on the sleeve bottom a central, extending in the direction of the longitudinal axis of the cartridge propellant charge igniter is arranged.
  • Such a cartridge is known for example from DE 41 38 269 A1.
  • the propellant charge igniter extends approximately to the rear end of the tail of the projectile.
  • only very short propellant charge igniter can be used, which can lead to uneven ignition propagation within the propellant charge.
  • a cartridge is also known, in which the tail has a rear side recess of shallow depth.
  • a shaped body is provided which extends into the recess of the tail and projects into the propellant charge body.
  • only relatively short propellants lighter can be used when the tail of the projectile extends far into the rear of the propellant charge sleeve into it.
  • the invention has for its object to provide a cartridge with a projectile, which has a rigid wing assembly with far rearwardly projecting wing tips, the length of the propellant charge igniter can be selected longer than this is the case with comparable known cartridges.
  • the invention is based essentially on the idea that the tail wings are connected only in a front portion with a tail boom and the rear side of the tail boom subsequent, surrounding the tail wings core area is used for receiving the propellant charge igniter.
  • a circumferentially provided with openings tubular sleeve is provided on which the rear-side areas of the tail wings are supported, wherein the peripheral and optionally frontal openings each have a diameter which is smaller is selected as the diameter of the Leitwerkshoffl surrounding Treibladungspulverkömer.
  • the tubular sleeve is the rear side outside the area through which the propellant charge igniter is inserted into the sleeve, closed by a partition which can be laterally connected to the combustible propellant charge sleeve, such that between the sleeve bottom and the partition a first partial charge is arranged and on the side of the chaff, a second partial charge connects to the first partial charge.
  • annular partial bodies arranged axially one behind the other into which the front area of the propellant charge igniter projects.
  • the mutual distance of the annular body part must then be chosen such that it is smaller than the diameter of the surrounding Leitwerk wing powder grains of the propellant charge.
  • the tubular sleeve or the annular body part may consist of a combustible material, but also of metal.
  • tubular sleeve or the annular part body are slotted on the outside in the axial direction such that the wing ends are supported in the circumferential direction on the wall regions of the corresponding slots.
  • Fig.1 denotes a cartridge.
  • This comprises a fixed to a sleeve bottom 2 two-piece propellant charge case 3 made of a combustible material and a projectile 4 with a far into the interior 5 of the propellant charge shell 3 reaching rigid tail 6.
  • At the bottom of the case 2 is a central, in the direction of the longitudinal axis 7 of the cartridge 1 extending propellant charge 8 arranged.
  • the tail wings 9 of the tail 6 are connected only in a front portion with a tail boom 10.
  • Rear side of the tailplane support 10 is replaced by a circumferentially provided with openings 11 tubular sleeve 12, in which the propellant charge igniter 8 extends.
  • the peripheral openings 11 of the tubular sleeve 12 have a diameter on, on the one hand should be as large as possible, so ignite the propellant charge 13 in the area of the tail unit 6 as undisturbed when igniting the propellant charge igniter 8.
  • the openings 11 may not be larger than the diameter of the powder grains of the corresponding propellant charge 13, so that no powder grains reach the interior of the tubular sleeve 12. The same applies to the front side between the tubular sleeve 12 and the tail unit 10 resulting opening 100th
  • the rear drive part 17 is closed by a partition wall 14 between the propellant charge sleeve 3 and the propellant charge igniter 8.
  • the partition wall 14 is laterally connected to the propellant charge case 3, such that between the sleeve bottom 2 and the partition wall 14, a first partial charge 15 is arranged and the second circuit side of the first partial charge 15, a second partial charge 16 is connected.
  • first the rear drive member 17 with sleeve bottom 2 first sleeve member 18 of the propellant charge shell 3, spring plate 19, circlip 20 and propellant charge 8 are connected and then filled the first partial charge 15 from above into the sleeve part and the rear drive part with the Partition 14 (eg a laboratory cloth made of silk) closed.
  • Partition 14 eg a laboratory cloth made of silk
  • the projectile 4 is turned upside down and the second sleeve part 22 is connected to a sleeve cover (not shown).
  • the tubular sleeve 12 (of combustible sleeve material, for example) is then pushed into the tail 6 and the second partial charge 16 is poured from above around the tubular sleeve 12 into the second sleeve part 22.
  • the front drive part 21 between the tubular sleeve 12 and the propellant charge tube 3 with a partition wall. In this case, finally, the front drive part 21 is then pushed onto the rear drive part 17, and the two sleeve parts are interconnected bonded.
  • Figures 2 and 3 show an alternative solution in which the tubular sleeve are replaced by a plurality of axially successively arranged, annular part body 23, wherein the mutual distance 24 adjacent part body 23 has a diameter which is smaller than the diameter of the tail wings. 9 surrounding powder grains of the propellant charge 13 is selected.
  • the annular part bodies 23 have slots 25 extending on the outside in the axial direction, so that the ends of the tail wings 9 are supported in the circumferential direction and stiffened against rotation.
  • slots 25 are also expendable, they simplify assembly and, e.g. the ability to easily connect the tail wings in each case via a press fit in the circumferential direction with the part bodies.
  • the part body 23 can also be connected to the freestanding lower edges of the tail wings by gluing, welding or soldering.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Switches With Compound Operations (AREA)
  • Air Bags (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)
EP05027946A 2004-12-22 2005-12-20 Cartouche Not-in-force EP1674817B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102004062931A DE102004062931A1 (de) 2004-12-22 2004-12-22 Patrone

Publications (2)

Publication Number Publication Date
EP1674817A1 true EP1674817A1 (fr) 2006-06-28
EP1674817B1 EP1674817B1 (fr) 2009-03-11

Family

ID=35539476

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05027946A Not-in-force EP1674817B1 (fr) 2004-12-22 2005-12-20 Cartouche

Country Status (4)

Country Link
EP (1) EP1674817B1 (fr)
AT (1) ATE425432T1 (fr)
DE (2) DE102004062931A1 (fr)
ES (1) ES2321628T3 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2911184A1 (fr) * 2007-01-10 2008-07-11 Nexter Munitions Sa Anneau elastique assurant le maintien d'un etui combustible
WO2009147349A1 (fr) 2008-05-12 2009-12-10 Hexacath Dispositif medical implantable avec un moyen de positionnement a un endroit precis d'embranchement d ' un vaisseau sanguin tel qu'une coronaire
WO2010055088A1 (fr) * 2008-11-13 2010-05-20 Ruag Ammotec Gmbh Allumeur pyrotechnique
RU2747558C1 (ru) * 2020-02-25 2021-05-06 Федеральное государственное казенное военное образовательное учреждение высшего образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" Способ увеличения дальности полета снаряда

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007039662B4 (de) 2007-08-22 2014-12-04 Rheinmetall Waffe Munition Gmbh Treibladungsanzünder

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE433653A (fr) *
US2793590A (en) * 1952-04-05 1957-05-28 Energa Practice projectile
US2872864A (en) * 1952-01-08 1959-02-10 Gladeon M Barnes Center-guide for fin-stabilized fixed round ammunition
DE3409017A1 (de) 1984-03-13 1985-09-26 Rheinmetall GmbH, 4000 Düsseldorf Patronierte munition fuer rohrwaffen
US4887534A (en) * 1988-06-10 1989-12-19 Honeywell Inc. Ignition system for high intrusion projectile
US4936219A (en) * 1989-08-10 1990-06-26 The United States Of America As Represented By The Secretary Of The Army Fin protection device
US20020124760A1 (en) * 2000-03-23 2002-09-12 Bernard Brion Primer tube for artillery ammunition

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE433653A (fr) *
US2872864A (en) * 1952-01-08 1959-02-10 Gladeon M Barnes Center-guide for fin-stabilized fixed round ammunition
US2793590A (en) * 1952-04-05 1957-05-28 Energa Practice projectile
DE3409017A1 (de) 1984-03-13 1985-09-26 Rheinmetall GmbH, 4000 Düsseldorf Patronierte munition fuer rohrwaffen
US4887534A (en) * 1988-06-10 1989-12-19 Honeywell Inc. Ignition system for high intrusion projectile
US4936219A (en) * 1989-08-10 1990-06-26 The United States Of America As Represented By The Secretary Of The Army Fin protection device
US20020124760A1 (en) * 2000-03-23 2002-09-12 Bernard Brion Primer tube for artillery ammunition

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2911184A1 (fr) * 2007-01-10 2008-07-11 Nexter Munitions Sa Anneau elastique assurant le maintien d'un etui combustible
EP1985965A1 (fr) * 2007-01-10 2008-10-29 NEXTER Munitions Anneau élastique assurant le maintien d'un étui combustible
US7644662B2 (en) 2007-01-10 2010-01-12 Nexter Munitions Elastic retention ring for combustible casings
WO2009147349A1 (fr) 2008-05-12 2009-12-10 Hexacath Dispositif medical implantable avec un moyen de positionnement a un endroit precis d'embranchement d ' un vaisseau sanguin tel qu'une coronaire
WO2010055088A1 (fr) * 2008-11-13 2010-05-20 Ruag Ammotec Gmbh Allumeur pyrotechnique
WO2010055086A1 (fr) * 2008-11-13 2010-05-20 Ruag Ammotec Gmbh Allumeur pyrotechnique
DE102009052578B4 (de) 2008-11-13 2021-09-30 Ruag Ammotec Gmbh Pyrotechnischer Anzünder
DE102009052753B4 (de) 2008-11-13 2022-01-20 Ruag Ammotec Gmbh Pyrotechnischer Anzünder
RU2747558C1 (ru) * 2020-02-25 2021-05-06 Федеральное государственное казенное военное образовательное учреждение высшего образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" Способ увеличения дальности полета снаряда

Also Published As

Publication number Publication date
ATE425432T1 (de) 2009-03-15
ES2321628T3 (es) 2009-06-09
EP1674817B1 (fr) 2009-03-11
DE102004062931A1 (de) 2006-07-06
DE502005006798D1 (de) 2009-04-23

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