EP0678725A1 - Vorrichtung zum Zünden einer Treibladung - Google Patents

Vorrichtung zum Zünden einer Treibladung Download PDF

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Publication number
EP0678725A1
EP0678725A1 EP95400556A EP95400556A EP0678725A1 EP 0678725 A1 EP0678725 A1 EP 0678725A1 EP 95400556 A EP95400556 A EP 95400556A EP 95400556 A EP95400556 A EP 95400556A EP 0678725 A1 EP0678725 A1 EP 0678725A1
Authority
EP
European Patent Office
Prior art keywords
projectile
jacket
propellant charge
ignition device
rear part
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.)
Withdrawn
Application number
EP95400556A
Other languages
English (en)
French (fr)
Inventor
Roland Boual
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.)
CTA International SAS
Original Assignee
CTA International SAS
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 CTA International SAS filed Critical CTA International SAS
Publication of EP0678725A1 publication Critical patent/EP0678725A1/de
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • 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
    • F42B5/045—Cartridges, i.e. cases with charge and missile of telescopic type
    • 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
    • F42B5/067—Mounting or locking missiles in cartridge cases
    • 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
    • F42C19/0807—Primers; Detonators characterised by the particular configuration of the transmission channels from the priming energy source to the charge to be ignited, e.g. multiple channels, nozzles, diaphragms or filters

Definitions

  • the technical field of the invention is that of devices for igniting a propellant charge of ammunition, in particular of the telescoped type.
  • Telescoped ammunition is characterized by the fact that the projectile is placed inside the envelope containing the propellant charge. This provision makes it possible to define shorter munitions, which allows the design of more compact weapons and / or at higher rates of fire.
  • the projectile is no longer stationed in the barrel of the weapon when the ammunition is placed in the chamber. It is the pressure of the gases generated by the combustion of the propellant charge which will first bring the projectile to station in the barrel of the weapon, then in a second time push it inside the tube.
  • Patent FR2647890 proposes in particular to have at the front of the ammunition a cap connecting the projectile to an annular ring secured to the casing of the ammunition. This device prevents any passage of gas at the front of the projectile, the cap being pushed by the combustion gases at the same time as the projectile.
  • the patent US4335657 describes a telescoped munition mechanically controlling the firing sequence of the propellant charge.
  • a piston acts as a barrier between the priming composition and the propellant charge.
  • the piston which has an axial stroke limited by a stop, slides while advancing the projectile until it is stationed. And it is only from this moment that the combustion gases of the primer can initiate the propellant charge through orifices released by the piston arriving at the end of the stroke.
  • Such a concept is particularly interesting because it makes it possible to ignite a propellant charge of telescoped ammunition in two stages, while protecting the fragile wall of the projectile.
  • the ignition device according to the invention ensures in a simple and effective way a two-stage ignition of the propellant charge, while not causing unnecessary increase in the mass of the ammunition.
  • the subject of the invention is a device for igniting a propellant charge contained in an envelope of a telescoped type of ammunition, comprising a jacket slidingly mounted in a tubular guide skirt integral with the envelope, a pyrotechnic composition d ignition arranged in an internal volume of the jacket and intended during its initiation to push a projectile which pulls the jacket, ignition device characterized in that the jacket is of tubular shape and has at its front end, a closing means made integral by an unlockable connecting means.
  • the means for closing the front end of the liner is produced by a rear part of the projectile, part penetrating into an internal clearance of the liner and the unlockable connecting means between the front end of the liner and the rear part of the projectile is an elastic ring resistant to a determined force.
  • the guide skirt has at its front end an annular flange which ensures the centering of the rear part of the projectile and the jacket has at its rear end a shoulder which guides it inside of the skirt, collar and shoulder which can cooperate after initiation of the pyrotechnic composition in order to produce an axial stop.
  • the jacket comprises at least one sealing means with the guide skirt, means comprising at least one seal disposed in a circular groove on the external surface of the shoulder.
  • the rear part of the projectile comprises at least one seal, arranged in a circular groove provided on the rear part and ensuring a seal with the jacket.
  • the ignition device for a propellant charge contained in an envelope closed at its front part by a guide tube whose internal housing has a diameter less than the external diameter of a projectile belt is characterized in that after initiation of the pyrotechnic composition, the shoulder of the shirt being in abutment against the collar of the skirt and the unlockable connecting means between the projectile and the shirt being released, the initiation of the propellant charge by the ignition pyrotechnic composition is only carried out when the projectile belt is engaged inside the internal housing of the guide tube in order to protect from the pressure generated by the gases of combustion of the propellant charge, a wall of the projectile located in front of the belt.
  • a telescoped munition 1 comprises a casing 2, preferably made of plastic or composite and closed at a rear end by a base 3, made of metallic material, which carries a primer 4 of the type known.
  • the envelope which contains a propellant charge 5 is closed at its front end by a guide tube 6 also made of metallic material.
  • a front seal 7 seals the propellant charge combustion gases under pressure, between the casing 2 and the guide tube 6, while a rear seal 8 seals between the casing and the base 3.
  • the base 3 receives integrally, for example by a threaded connection, a metal guide skirt 9.
  • the latter of tubular shape, has a bore 10 limited towards the front by an annular flange 11 of internal diameter smaller than that of bore 10.
  • a jacket 12 metallic and also of tubular shape, comprises on its external face a cylindrical surface 13 and a shoulder 14 located at its rear end.
  • the jacket is slidably mounted inside the skirt 9.
  • the shoulder 14 and the bore 10 on the one hand, and the cylindrical seat 13 and the flange 11 on the other hand, have sliding adjustments.
  • An O-ring seal 19 is placed in a circular groove in the shoulder 14 and provides a static and dynamic seal against the gases generated by an ignition composition 25, between the jacket 12 and the skirt 9.
  • the latter has a sliding fit with an internal housing 27 of the guide tube 6.
  • Such a cap is described in patent FR2647890.
  • a rear part 16 of the projectile 15 is made integral with the jacket 12, at the level of an internal clearance 21 produced at the front end of the latter and thus constitutes a means for closing the jacket 12.
  • This connection is here ensured by an elastic ring 20 which is housed in corresponding grooves arranged on the projectile and the jacket.
  • the ring constitutes an unlockable connection means between the rear part of the projectile and the jacket.
  • An O-ring seal 22 is placed in a groove in the rear part of the projectile and is supported on the internal clearance 21. It provides gas tightness between the projectile and the jacket 12.
  • the volume defined by an internal diameter 23 of the jacket, the rear part 16 of the projectile and the primer is filled with the pyrotechnic ignition composition 25 intended to push the projectile forward.
  • the rear part 16 of the projectile thus constitutes a means of closing the jacket which delimits a maximum volume for the pyrotechnic composition without causing a penalizing increase in the inert mass.
  • the projectile 15 has on its outside diameter a belt 26 intended to take the scratches from the barrel of a weapon not shown.
  • the outer wall 28 of the projectile (here of the explosive / fragmentable type), which is located in front of the belt, is thin and therefore fragile. It must not be subjected to the pressure generated by the combustion gases of the propellant charge 5, which would risk damaging it and causing a premature explosion.
  • Figure 2 shows the telescoped ammunition 1 after firing.
  • the primer 4 initiated by percussion or electrically, ignites the pyrotechnic composition 25.
  • the combustion of the latter generates pressure on the rear part 16 of the projectile 15 which pushes the projectile 15 / jacket 12 assembly towards the front of the munition .
  • the shoulder 14 of the jacket comes into abutment against the annular collar 11 of the skirt 9, the pressure of the combustion gases increases until the breaking or release of the unlockable connecting means 20 between the projectile and the jacket.
  • the groove of the projectile in which the elastic ring 20 is mounted has a depth substantially equal to the diameter of the ring, while the groove made in the clearance 21 of the jacket has a depth slightly greater than the diameter of the ring.
  • the elastic ring 20 which is mounted substantially at the bottom of the groove of the projectile, opens and is housed entirely in the groove of the release 21 of the shirt.
  • the projectile which is no longer retained, then continues to advance while still being guided and centered by the release 21, which ensures that the projectile is correctly placed in the barrel of the weapon.
  • the projectile belt 26 engages in the housing 27 of the guide tube.
  • the adjustment of the belt 26 in the guide tube 6 is tight.
  • the fragile wall of the projectile situated in front of the belt is protected from the pressure of the combustion gases of the propellant charge 5 by the guide tube 6.
  • the cap 18 engages inside the barrel of the weapon.
  • the cap is broken at the exit of the tube under the effect of aerodynamic forces.
  • the dimensioning of the constituent parts of the device according to the invention will be carried out in such a way that the force necessary for breaking or releasing the unlockable projectile / shirt connecting means is greater than that due to the translation of the shirt in the skirt, but less than the resistance of the axial stop between the flange 11 and the shoulder 14.
  • FIG. 3 represents the telescoped munition 1 at the time of ignition of the propellant charge 5 by the ignition pyrotechnic composition 25, when the rear part 16 of the projectile constituting the closing means leaves the jacket 12.
  • the ignition is thus effected by the front opening of the jacket 12, which is released by the separation of the rear part 16 of the projectile.
  • the ignition of the propellant charge is therefore carried out in two stages and the second stage does not begin until the belt 26 of the projectile has penetrated inside the guide tube 6, which makes it possible to provide effective protection of the fragile wall of the projectile.
  • the guide tube 6 will be dimensioned in such a way that it cannot in any case, under the rise in pressure of the combustion gases of the propellant charge, shrink on the wall 28 of the projectile whose diameter is less than that of the belt.
  • unlockable connection between the sleeve 12 and the rear part 16 of the projectile can be provided by other means than an elastic ring, for example by shearable pins.
EP95400556A 1994-03-16 1995-03-15 Vorrichtung zum Zünden einer Treibladung Withdrawn EP0678725A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9403063 1994-03-16
FR9403063A FR2717569B1 (fr) 1994-03-16 1994-03-16 Dispositif d'allumage d'une charge propulsive.

Publications (1)

Publication Number Publication Date
EP0678725A1 true EP0678725A1 (de) 1995-10-25

Family

ID=9461101

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95400556A Withdrawn EP0678725A1 (de) 1994-03-16 1995-03-15 Vorrichtung zum Zünden einer Treibladung

Country Status (2)

Country Link
EP (1) EP0678725A1 (de)
FR (1) FR2717569B1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3098292B1 (fr) * 2019-07-04 2021-07-23 Cta Int Munition télescopée comprenant un obus

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4335657A (en) * 1980-08-13 1982-06-22 Ford Aerospace & Communications Corp. Ammunition round with retained piston
WO1986005265A1 (en) * 1985-03-05 1986-09-12 Nico-Pyrotechnik Hanns-Jürgen Diederichs Gmbh & Co Cartridged ammunition
US4782758A (en) * 1986-02-03 1988-11-08 Aerojet-General Corporation Ammunition round
FR2647890A1 (fr) * 1989-06-01 1990-12-07 France Etat Armement Dispositif de maintien d'un projectile relativement a l'enveloppe d'une munition telescopee
US5173571A (en) * 1987-12-28 1992-12-22 Montgomery Donald N Projectile guide for telescoped ammunition

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4335657A (en) * 1980-08-13 1982-06-22 Ford Aerospace & Communications Corp. Ammunition round with retained piston
WO1986005265A1 (en) * 1985-03-05 1986-09-12 Nico-Pyrotechnik Hanns-Jürgen Diederichs Gmbh & Co Cartridged ammunition
US4782758A (en) * 1986-02-03 1988-11-08 Aerojet-General Corporation Ammunition round
US5173571A (en) * 1987-12-28 1992-12-22 Montgomery Donald N Projectile guide for telescoped ammunition
FR2647890A1 (fr) * 1989-06-01 1990-12-07 France Etat Armement Dispositif de maintien d'un projectile relativement a l'enveloppe d'une munition telescopee

Also Published As

Publication number Publication date
FR2717569A1 (fr) 1995-09-22
FR2717569B1 (fr) 1996-05-10

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