EP2703769A1 - Vorrichtung zum Entschliessen einer Munitionshülse - Google Patents

Vorrichtung zum Entschliessen einer Munitionshülse Download PDF

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Publication number
EP2703769A1
EP2703769A1 EP13180938.6A EP13180938A EP2703769A1 EP 2703769 A1 EP2703769 A1 EP 2703769A1 EP 13180938 A EP13180938 A EP 13180938A EP 2703769 A1 EP2703769 A1 EP 2703769A1
Authority
EP
European Patent Office
Prior art keywords
ring
rocket
envelope
fuse
ammunition
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
EP13180938.6A
Other languages
English (en)
French (fr)
Other versions
EP2703769B1 (de
Inventor
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
Application filed by Nexter Munitions SA filed Critical Nexter Munitions SA
Priority to PL13180938T priority Critical patent/PL2703769T3/pl
Publication of EP2703769A1 publication Critical patent/EP2703769A1/de
Application granted granted Critical
Publication of EP2703769B1 publication Critical patent/EP2703769B1/de
Active 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
    • 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 ammunition rockets which are intended to ensure the initiation of an explosive charge placed in an envelope and more particularly rockets that can also ensure a deconfinement of the ammunition envelope as a result to a warm-up, for example during a fire.
  • the patent US7025000 describes a projectile for which the rocket is linked to the projectile body by a fusible plastic ring.
  • the ring carries a tapping receiving the rocket and a thread engaged in the projectile body. This ring alone ensures the mechanical strength of the projectile rocket link during firing and it also ensures the deconfinement by its melting during the rise in temperature.
  • This device has disadvantages. It is thus difficult to find a material that can both withstand the shooting and handling constraints of the projectile and can also melt quickly and reproducibly to release the rocket.
  • the patent EP2079980 proposes a connecting ring which is interposed between the projectile body and the rocket. This ring carries an intermediate ring which receives the rocket. During a rise in the pressure in the ammunition body, the intermediate ring is sheared and releases the rocket.
  • the invention aims to provide a rocket incorporating means ensuring its deconfinement, means having a reduced radial size.
  • the means of the invention provide deconfinement in a reliable and reproducible manner while not weakening the mechanical strength of the rocket / projectile link to firing constraints (axial and angular accelerations).
  • the invention relates to a firing rocket intended to be secured to a shell of a munition containing an explosive charge rocket characterized in that it comprises a smooth outer cylindrical surface on which is slidably positioned a ring bearing a thread on its outer surface, thread intended to cooperate with a tapping of the ammunition envelope, the ring being made integral in rotation with the body of the rocket by at least one longitudinal key, the rocket also carrying a rod shear forming an axial stop for the ring during the sliding thereof after mounting the rocket on the envelope.
  • the ring may have an annular shape and be housed in a groove of the rocket.
  • the ring may include a counterbore coming to cap the ring during screwing.
  • the ring may be made of steel.
  • the ring may be made of a synthetic material.
  • a firing rocket 1 according to the invention is shown integral with an envelope 2a of a munition 2 which defines an internal cavity 2b enclosing an explosive charge (not shown).
  • the ammunition 2 is for example an artillery shell.
  • the rocket 1 is shown schematically here, because the characteristics thereof being the subject of the invention are relative to the only means for fixing it to the casing 2a of the ammunition.
  • the rocket has a front portion 1a ogivée, which is schematized in part dashed, and which contains electronic or mechanical means for its operation: safety device and armament, electronic components associated with the firing control (according to the case: chronometry, proximetry), pyrotechnic priming components and their means of initiation.
  • the rear part 1b of the fuse 1 which is engaged in the internal cavity 2b of the ammunition conventionally contains a pyrotechnic detonation relay (not shown).
  • the rocket 1 is thus uniformly hatched to simplify the representation. This hatching does not prejudge the internal structure of the rocket which is neither represented nor described.
  • the rocket 1 has an outer smooth cylindrical bearing surface 3, of longitudinal axis 8, on which is slidably positioned a ring 4 carrying a thread 4a on its outer surface.
  • This thread 4a is intended to cooperate with a complementary tapping 5 carried by the shell 2a of ammunition (see also FIG. figure 3 ).
  • the ring 4 is also made integral in rotation with the body of the rocket 1 by at least one longitudinal key 6 (here there are four longitudinal keys, regularly distributed angularly).
  • each key 6 is housed in a recess 7 machined in the body of the fuse 1 and having a shape complementary to that of the key 6.
  • the keys and their fingerprints 7 have hemicylindrical ends, this for ease of machining.
  • the keys 6 are immobilized in translation by the impressions 7 in a direction parallel to the axis 8 of the rocket.
  • the ring 4 comprises longitudinal grooves 9 which each receive one of the keys 6. These grooves 9 are open from one end to the other of the ring 4. Thus, when the ring 4 is positioned on the cylindrical seat 3, it slides freely in the axial direction 8 and is integral in rotation with the rocket by the keys 6 which interpose between the grooves 9 of the ring 4 and the footprints 7 of the rocket.
  • the rocket 3 finally carries a shearable annular ring 10 which is positioned in a circular groove 11 of the rocket 1.
  • the ring 10 is made of a synthetic material, for example polytetrafluoroethylene (PTFE). It is put in place in its groove 11 by mechanical deformation.
  • PTFE polytetrafluoroethylene
  • the ring 10 forms an axial stop for the ring 4 during sliding thereof.
  • the ring 4 comprises at each end a countersink 12.
  • the counterbores have a diameter slightly greater than that of the ring 10.
  • one of the counterbores 12 caps the ring 10 (as shown figure 4b ).
  • the ring can slide because there is an axial clearance E ( figure 4a ) between the ring 4 and its housing on the seat 3, housing which has a total length P between the rod 12 and a shoulder 13 of the rocket 1.
  • the rocket according to the invention is mounted conventionally by screwing at the tapping 5 of a shell 2a of ammunition.
  • the thread of the rocket is no longer a fixed thread relative to the rocket body but a thread carried by a sliding ring 4.
  • the keys 6 prevent rotation of the ring which allows a first screwing step until abutment of the shoulder 13 of the rocket against the end of the casing 2a (see figure 4a ).
  • the screwing is no longer possible and the rocket 1 is immobilized relative to the envelope 2a.
  • a conventional solution such as a drop of glue deposited before screwing and which will dry, thus blocking the screwing, or a net stop mechanical as a radial screw engaged through the casing 2a and stopping at the thread 4a.
  • the gas pressure (arrow HP) that develops in the internal cavity 2b will be exerted on the rear part 1b of the rocket.
  • the ring 10 will be sheared and the rocket 1 will be ejected, thus ensuring deconfinement of the munition.
  • the ring 4 is made of a resistant material, for example steel.
  • the projectile rocket link is via the ring 4 and the keys 6 also made of steel.
  • the mechanical strength of this connection is excellent and the radial size of the ring is reduced (ring thickness less than 5 mm).
  • the deconfining depends only on the shear strength characteristics of the rod 10 which is dimensioned accordingly and which is made of a material chosen to be sheared at a given stress level. Furthermore the material of the ring may be softened by heating which will facilitate deconfinement.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Injection Moulding Of Plastics Or The Like (AREA)
EP13180938.6A 2012-08-29 2013-08-19 Vorrichtung zum Entschliessen einer Munitionshülse Active EP2703769B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL13180938T PL2703769T3 (pl) 2012-08-29 2013-08-19 Zapalnik zapłonowy pozwalający na zwolnienie obudowy amunicji

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1202326A FR2995075B1 (fr) 2012-08-29 2012-08-29 Fusee d'amorcage permettant le deconfinement d'une enveloppe de munition

Publications (2)

Publication Number Publication Date
EP2703769A1 true EP2703769A1 (de) 2014-03-05
EP2703769B1 EP2703769B1 (de) 2015-12-23

Family

ID=47710208

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13180938.6A Active EP2703769B1 (de) 2012-08-29 2013-08-19 Vorrichtung zum Entschliessen einer Munitionshülse

Country Status (4)

Country Link
EP (1) EP2703769B1 (de)
ES (1) ES2562202T3 (de)
FR (1) FR2995075B1 (de)
PL (1) PL2703769T3 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200191538A1 (en) * 2018-12-13 2020-06-18 Thales Device for venting an explosive charge and munition equipped with such a device
US11193743B1 (en) * 2020-06-04 2021-12-07 The United States Of America, As Represented By The Secretary Of The Navy Cook-off mitigation system

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2742221A1 (fr) * 1995-12-12 1997-06-13 Soc D Ateliers Mecaniques De P Dispositif de deconfinement pour munition
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
EP2079980A2 (de) 2006-09-29 2009-07-22 NEXTER Munitions Vorrichtung zum entschliessen einer munitionshülse
WO2011101545A1 (en) * 2010-02-19 2011-08-25 Patria Land Services Oy Lifting member for projectiles

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2742221A1 (fr) * 1995-12-12 1997-06-13 Soc D Ateliers Mecaniques De P Dispositif de deconfinement pour munition
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
EP2079980A2 (de) 2006-09-29 2009-07-22 NEXTER Munitions Vorrichtung zum entschliessen einer munitionshülse
WO2011101545A1 (en) * 2010-02-19 2011-08-25 Patria Land Services Oy Lifting member for projectiles

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200191538A1 (en) * 2018-12-13 2020-06-18 Thales Device for venting an explosive charge and munition equipped with such a device
US11054229B2 (en) * 2018-12-13 2021-07-06 Thales Device for venting an explosive charge and munition equipped with such a device
US11193743B1 (en) * 2020-06-04 2021-12-07 The United States Of America, As Represented By The Secretary Of The Navy Cook-off mitigation system

Also Published As

Publication number Publication date
ES2562202T3 (es) 2016-03-03
EP2703769B1 (de) 2015-12-23
PL2703769T3 (pl) 2016-07-29
FR2995075B1 (fr) 2014-08-29
FR2995075A1 (fr) 2014-03-07

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