EP2079980A2 - Vorrichtung zum entschliessen einer munitionshülse - Google Patents

Vorrichtung zum entschliessen einer munitionshülse

Info

Publication number
EP2079980A2
EP2079980A2 EP07848252A EP07848252A EP2079980A2 EP 2079980 A2 EP2079980 A2 EP 2079980A2 EP 07848252 A EP07848252 A EP 07848252A EP 07848252 A EP07848252 A EP 07848252A EP 2079980 A2 EP2079980 A2 EP 2079980A2
Authority
EP
European Patent Office
Prior art keywords
ring
rocket
connecting ring
intermediate ring
projectile
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
EP07848252A
Other languages
English (en)
French (fr)
Other versions
EP2079980B1 (de
Inventor
Stéphane Cotet
Laurent Desgland
Dominique Dion
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.)
Nexter Munitions SA
Original Assignee
Nexter Munitions SA
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=38005783&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2079980(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Nexter Munitions SA filed Critical Nexter Munitions SA
Publication of EP2079980A2 publication Critical patent/EP2079980A2/de
Application granted granted Critical
Publication of EP2079980B1 publication Critical patent/EP2079980B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
    • F42B39/20—Packages or ammunition having valves for pressure-equalising; Packages or ammunition having plugs for pressure release, e.g. meltable ; Blow-out panels; Venting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/02—Fuze bodies; Fuze housings

Definitions

  • the technical field of the invention is that of the devices ensuring the deconfinement of a munition envelope containing an explosive charge and more particularly the deconfining devices for an explosive projectile body, whatever the caliber or the type of weapon pulling this projectile.
  • the deconfinement devices make it possible to avoid, for example, the detonation of a projectile as a result of a heating, for example during a fire.
  • the patent DE2131748 thus describes a closure cap of a projectile body which is put in place when the projectile is stored.
  • This plug has a closure plate which is connected by a fusible material. The temperature rise releases the plate which allows the evacuation of gases.
  • the heating can lead both to the initiation of the load itself as a result of the increase in pressure, the initiation of the rocket which also causes the detonation of the explosive charge.
  • a device for ensuring deconfinement when the rocket is mounted on the body of the projectile is also known from the patent FR2864219 .
  • This device comprises a connecting ring ensuring the connection of the rocket and the projectile ring which carries radial vents within which are arranged silicone plugs.
  • this device is however insufficiently effective because the total area of the vents is too small and does not ensure rapid deconfinement of the inside of the body of the projectile.
  • Such a device is complex because it implements a spring maintained in the compressed state.
  • the mechanical strength of the fuse material is also not ensured especially after long storage phases, which penalizes the reliability of this device.
  • DE4336808 discloses an impact marking projectile comprising an ejection rocket on trajectory by the action of a specific pyrotechnic charge.
  • a projectile does not have an explosive charge.
  • the problem of protecting a load against temperature rises does not arise.
  • the structure described is not suitable for initiating an explosive charge.
  • the object of the invention is to provide a deconfining device that makes it possible in a simple and reliable manner to provide effective protection against accidental initiations due to the heating of the explosive charge of an ammunition and in particular of a projectile. artillery.
  • the device according to the invention ensures in particular this function even when the rocket is mounted on the body of the projectile.
  • the device according to the invention does not, however, interfere with the normal operation of the munition, ie the initiation of the explosive charge by the rocket.
  • the subject of the invention is a device for deconfining an envelope of a munition containing an explosive charge that can be initiated by a firing rocket, a device comprising a connecting ring connected to the envelope and making it possible to secure the rocket.
  • priming device to the casing characterized in that it comprises a means ensuring a weakened and shearable connection between the fuse and the connecting ring, which connection is sheared as a result of an increase in the pressure inside.
  • the connecting ring having a bottom forming a projectable plate on the explosive charge during the initiation of the rocket, bottom may also be broken by the appearance of pressure within the body of the projectile .
  • the shearable connection means may comprise an intermediate ring which is interposed between the connecting ring and the rocket, which ring is connected to the rocket or to the connecting ring by a shearable element.
  • the intermediate ring may comprise an internal thread for receiving the rocket, the shearable element being disposed at an outer surface of the intermediate ring.
  • the shearable element of the intermediate ring may comprise at least one peripheral toothing intended to be housed in a complementary groove carried by the connecting ring.
  • the intermediate ring may comprise at least two longitudinal grooves delimiting radially deformable nozzles, the deformation of the nozzles allowing the establishment of the teeth in their grooves during attachment of the intermediate ring on the connecting ring.
  • the intermediate ring has more particularly at least one longitudinal tongue carried by its outer surface, tongue intended to be housed in a complementary groove carried by the connecting ring, and S ensuring immobilization in rotation of the intermediate ring relative to the ring connection.
  • the bottom may comprise at least one circular groove ensuring a decrease in its thickness.
  • FIG. 1 is a partial diagrammatic longitudinal section of a front part of a projectile equipped with a device according to one embodiment of the invention
  • FIGS. 2a, 2b, 2c and 2d show an exemplary embodiment of an intermediate ring of a device according to the invention, the ring being shown in an external view in FIGS. 2a and 2b and in longitudinal section in FIG. , section taken along the plane whose track AA is marked in Figure 2b, Figure 2d is also a perspective view of the ring, Figures 3a and 3b show the intermediate ring assembled to the connecting ring, Figure 5 3a being a perspective view of this assembly and Figure 3b a longitudinal sectional view, Figure 4 finally shows schematically the operation of the device according to the invention.
  • FIG. 1 shows in partial longitudinal section the front portion of a munition 1 which is an artillery projectile.
  • This projectile is represented here schematically. It comprises an envelope or body 2 enclosing an explosive charge 3. Its front part AV carries a rocket
  • the explosive charge 3 also bears at its surface before a tablet 4 of an explosive priming composition.
  • a connecting ring 7 is connected to the body 2 of the projectile by a thread.
  • This connecting ring has a bottom 8 forming a projectable plate on the explosive charge 3; 4 at the initiation of the rocket 5.
  • the bottom 8 will advantageously comprise at least one circular groove 9 (see Figure 3b) which ensures a reduction in its thickness. This groove is obtained by machining a bottom face. It thus forms a zone of reduced thickness for the bottom 8.
  • the ring 7 is made of steel.
  • the thickness of the connecting ring at the bottom 8 is about 1 mm.
  • the initiation of the rocket 5 causes a cut of the bottom 8 at the groove 9.
  • the fuze 5 is fixed to the connecting ring 7 by means of a connecting means which comprises an intermediate ring 10 interposed between the connecting ring 7 and the fuze 5.
  • This intermediate ring 10 is connected to the rocket or connecting ring by a shearable element.
  • FIGS. 2a to 2d show more precisely the structure of the intermediate ring 10
  • This ring 10 is open at both ends. It comprises an internal thread 11 which makes it possible to screw the rocket 5.
  • the intermediate ring 10 is made for example of plastic material. Depending on the operational constraints another material may be envisaged, for example brass.
  • the intermediate ring 10 has at its outer cylindrical surface 12 two peripheral peripheral teeth 13.
  • Each toothing 13 has in section a trapezoidal profile (see FIG. 2c) having an inclined flank 14 and a flank 15 straight and substantially perpendicular to the axis 16 of the ring 10.
  • the inclined side 14 is disposed at a front face 17 of the ring 10.
  • teeth 13 are intended to be housed in complementary grooves 18, which are carried by the connecting ring 7 (see Figure 3b).
  • the intermediate ring 10 further comprises at least two longitudinal slots 19 which extend over substantially half of the total height of the ring 10 and which delimit radially deformable nozzles 20.
  • the deformation of the nozzles 20 allows the insertion of the intermediate ring 10 into the connecting ring 7.
  • the slats 20 slide and deform radially without difficulty. They resume by their elasticity their initial position when the teeth 13 are in their grooves 18.
  • the intermediate ring 10 comprises longitudinal tongues 21 which are carried by its outer surface 12.
  • tongues are intended to be housed in complementary grooves 22 carried by the connecting ring 7 (see Figures 3a and 3b).
  • the tongues 21 make it possible to immobilize the intermediate ring 10 in rotation with respect to the connecting ring 7.
  • the intermediate ring 10 is thus after assembly completely integral both in rotation and in translation of the connecting ring 7. This avoids any risk of relative vibration of one ring relative to the other and the risks of unscrewing the rocket 5 that could result.
  • tongues 21 could be implemented keys that would be housed in grooves of the intermediate ring and the connecting ring.
  • Figures 3a and 3b show the intermediate ring 10 fixed to the connecting ring 7.
  • the spouts 13 constitute a shearable element ensuring a connection between the two rings 7 and 10.
  • the nozzles 20 can no longer deform radially. Furthermore, the right flanks 15 of the teeth 13 prevent any extraction of the intermediate ring 10.
  • the number and dimensions of the teeth 13 are chosen according to the minimum pressure at which it is desired to ensure the deconfinement of the projectile.
  • FIG. 4 thus shows the projectile 1 after rupture of the teeth 13.
  • the rocket 5 carries with it a portion of the intermediate ring 10.
  • the teeth 13 remain in their grooves 18.
  • the ejection of the rocket 5 leads to the opening of the hole 23 for filling the projectile 1.
  • the deconfinement is provided with an opening which is maximum for the evacuation of gases G.
  • the deconfining device thus makes it possible to ensure in a simple and reliable manner the protection of a projectile equipped with a firing rocket.
  • an intermediate ring 10 comprising, in place of the circular teeth 13, a shearable thread cooperating with a thread formed inside the connecting ring 7.
  • the shearable connection means will be constituted by a particular tapping of the inside of the connecting ring 7.
  • This tapping will be defined in such a way as to shear at the occurrence of an internal pressure exceeding a certain threshold.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Processing And Handling Of Plastics And Other Materials For Molding In General (AREA)
  • Placing Or Removing Of Piles Or Sheet Piles, Or Accessories Thereof (AREA)
  • Processing Of Solid Wastes (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Electrophotography Configuration And Component (AREA)
  • Lifting Devices For Agricultural Implements (AREA)
  • Fuses (AREA)
  • Food-Manufacturing Devices (AREA)
  • Wrapping Of Specific Fragile Articles (AREA)
  • Packages (AREA)
EP07848252A 2006-09-29 2007-09-19 Vorrichtung zum entschliessen einer munitionshülse Active EP2079980B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0608681A FR2906606B1 (fr) 2006-09-29 2006-09-29 Dispositif de deconfinement d'une enveloppe d'une munition.
PCT/FR2007/001518 WO2008040860A2 (fr) 2006-09-29 2007-09-19 Dispositif de deconfinement d'une enveloppe d'une munition

Publications (2)

Publication Number Publication Date
EP2079980A2 true EP2079980A2 (de) 2009-07-22
EP2079980B1 EP2079980B1 (de) 2010-03-17

Family

ID=38005783

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07848252A Active EP2079980B1 (de) 2006-09-29 2007-09-19 Vorrichtung zum entschliessen einer munitionshülse

Country Status (8)

Country Link
US (1) US7930975B2 (de)
EP (1) EP2079980B1 (de)
AT (1) ATE461417T1 (de)
DE (1) DE602007005394D1 (de)
ES (1) ES2342856T3 (de)
FR (1) FR2906606B1 (de)
IL (1) IL197816A (de)
WO (1) WO2008040860A2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2703769A1 (de) 2012-08-29 2014-03-05 Nexter Munitions Vorrichtung zum Entschliessen einer Munitionshülse

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2922638B1 (fr) * 2007-10-23 2013-07-05 Tda Armements Sas Chargement energetique a deconfinement controle et munition equipee d'un tel chargement
US8381657B1 (en) * 2008-10-24 2013-02-26 The United States Of America As Represented By The Secretary Of The Army Enhanced grenade
FR2948186B1 (fr) 2009-07-17 2015-02-20 Tda Armements Sas Munition comprenant des moyens pour neutraliser son chargement explosif
FI122080B (fi) * 2010-02-19 2011-08-15 Patria Land & Armament Oy Nostoelin ammuksia varten
US8381656B1 (en) * 2011-09-09 2013-02-26 The United States Of America As Represented By The Secretary Of The Army Mechanical cartridge and grenade venting
RU2479824C1 (ru) * 2011-09-12 2013-04-20 Открытое акционерное общество "Производственное объединение "Завод имени Серго" Боевая часть снаряда
US8505458B1 (en) * 2012-01-27 2013-08-13 The United States Of America As Represented By The Secretary Of The Navy Venting cap system
DE102013014811B4 (de) * 2013-09-05 2015-04-09 Diehl Bgt Defence Gmbh & Co. Kg Geschoss
US9410782B2 (en) * 2014-04-18 2016-08-09 Nostromo Holdings, Llc Multi-action fuze and warhead separator fitted to a munition
DE102014013316B4 (de) * 2014-09-08 2016-04-07 Diehl Bgt Defence Gmbh & Co. Kg Behältnis zur Aufbewahrung eines Explosivstoffs
US10101139B1 (en) * 2016-12-15 2018-10-16 The United States Of America As Represented By The Secretary Of The Navy Cook-off mitigation systems
US10724836B1 (en) * 2016-12-15 2020-07-28 The United States Of America, As Represented By The Secretary Of The Navy Cook-off mitigation systems
US10088285B1 (en) * 2016-12-15 2018-10-02 The United States Of America As Represented By The Secretary Of The Navy Cook-off mitigation systems using an uncanistered outgassing pad
FR3090086B1 (fr) * 2018-12-13 2020-12-11 Thales Sa Dispositif de deconfinement d’un chargement explosif et munition equipee d’un tel dispositif
CN109974544B (zh) * 2019-04-26 2024-02-06 中国工程物理研究院电子工程研究所 弹引连接结构及起爆装置

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
CH167210A (fr) * 1933-06-07 1934-02-15 Schwob Freres & Cie Sa Carter pour mécanisme de fusée mécanique.
GB964556A (en) * 1962-06-29 1964-07-22 Carl Olaf Julius Nordzell Ammunition safety device
DE2131748A1 (de) 1971-06-25 1972-12-28 Foerenade Fabriksverken Schutzvorrichtung fuer Granaten
DE3373938D1 (en) * 1982-03-04 1987-11-05 Royal Ordnance Plc Improvements in or relating to safety devices for carrier shells
US5035181A (en) * 1985-01-22 1991-07-30 The United States Of America As Represented By The Secretary Of The Navy Thermosensitive pop-out device
FR2686410A1 (fr) * 1992-01-22 1993-07-23 France Etat Armement Dispositif assurant le deconfinement d'une charge contenant un explosif par mise en óoeuvre d'un element deformable en materiau a memoire de forme.
DE4336808C2 (de) * 1993-10-28 1997-07-10 Buck Chem Tech Werke Prüfgeschoß zum Anzeigen der Zündfunktion eines Geschosses
FR2742221B1 (fr) * 1995-12-12 1998-02-27 Soc D Ateliers Mecaniques De P Dispositif de deconfinement pour munition
FR2781877A1 (fr) * 1998-07-30 2000-02-04 Giat Ind Sa Dispositif d'amorcage pour obus explosif
US7025000B1 (en) * 2002-04-11 2006-04-11 The United States Of America As Represented By The Secretary Of The Army Mechanism for reducing the vulnerability of high explosive loaded munitions to unplanned thermal stimuli
FR2864219B1 (fr) * 2003-12-22 2006-02-24 Giat Ind Sa Dispositif de deconfinement d'une enveloppe de munition

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008040860A2 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2703769A1 (de) 2012-08-29 2014-03-05 Nexter Munitions Vorrichtung zum Entschliessen einer Munitionshülse
FR2995075A1 (fr) * 2012-08-29 2014-03-07 Nexter Munitions Fusee d'amorcage permettant le deconfinement d'une enveloppe de munition

Also Published As

Publication number Publication date
WO2008040860A2 (fr) 2008-04-10
IL197816A (en) 2013-07-31
FR2906606A1 (fr) 2008-04-04
FR2906606B1 (fr) 2010-12-31
US7930975B2 (en) 2011-04-26
ES2342856T3 (es) 2010-07-15
DE602007005394D1 (de) 2010-04-29
EP2079980B1 (de) 2010-03-17
ATE461417T1 (de) 2010-04-15
IL197816A0 (en) 2009-12-24
WO2008040860A3 (fr) 2008-05-22
US20100024675A1 (en) 2010-02-04

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