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EP3136043B1 - Zünder eines sprengkopfs mit schlagbolzen - Google Patents

Zünder eines sprengkopfs mit schlagbolzen Download PDF

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Publication number
EP3136043B1
EP3136043B1 EP16185058.1A EP16185058A EP3136043B1 EP 3136043 B1 EP3136043 B1 EP 3136043B1 EP 16185058 A EP16185058 A EP 16185058A EP 3136043 B1 EP3136043 B1 EP 3136043B1
Authority
EP
European Patent Office
Prior art keywords
recess
rocket
striker
fuze
target
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
EP16185058.1A
Other languages
English (en)
French (fr)
Other versions
EP3136043A1 (de
Inventor
Nicolas Caillaut
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.)
KNDS Ammo France 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
Publication of EP3136043A1 publication Critical patent/EP3136043A1/de
Application granted granted Critical
Publication of EP3136043B1 publication Critical patent/EP3136043B1/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
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C1/00—Impact fuzes, i.e. fuzes actuated only by ammunition impact
    • F42C1/02—Impact fuzes, i.e. fuzes actuated only by ammunition impact with firing-pin structurally combined with fuze
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/04—Protective caps

Definitions

  • the technical field of the invention is that of rocket warhead firing pins.
  • warhead rockets as described in the patent US5243912 include a striker for striking a primer to trigger the payload of the projectile.
  • the strike movement of the striker at its first end is due to the impact pressure of the target material on the second end of the striker located at the front tip of the rocket.
  • This type of operation finds its limits during the treatment of so-called soft targets such as when one draws in sand or soft earth and that one however wishes an immediate release on the surface of the target.
  • the patent US1781556 discloses a rocket intended to be fired in soft ground.
  • the rocket has a cylindrical recess coaxial with the rocket whose bottom comprises a pusher for pushing a striker under the action of the constituent material of the target having penetrated by a front entrance of the recess at the moment of impact on the target.
  • the invention therefore aims to increase the operating sensitivity of rockets when the projectile is fired on soft targets.
  • the invention relates to a firing pin flare, the striker being oriented so as to impact the impact on a target a primer of the rocket towards the rear of the rocket, the rocket comprising an envelope whose tip has a recess of which an entry is open to allow the filling of the recess by the material of the impacted target, the bottom of the recess being breakable along its periphery and can be broken by the pressure exerted by the material of the target, the bottom can then push the striker towards the rear of the rocket, characterized in that the diameter of the inlet of the recess is smaller than the diameter of the periphery of the bottom of the recess.
  • the bottom is weakened at its connection with the envelope by a thinning of its periphery.
  • the rocket may include an intermediate pusher between the bottom and the striker, push for transmitting the bottom pressure on the striker.
  • the pusher may comprise an enlarged head whose profile is close to the internal surface of the warhead.
  • the opening of the recess is plugged by a seal designed to optimize the aerodynamic characteristics of the ogive.
  • the bottom may comprise an axial point extending inside the recess.
  • a rocket 1 has an envelope 2 ogive.
  • the rocket 1 is intended to be fixed to the front of a gyrating projectile (projectile not shown).
  • the rocket 1 comprises a primer 3 located in a safety and arming device comprising a rotor 4 disposed in a cage 22 rotatably mounted relative to the axis 7 of the rocket on journals.
  • the function of the rotor 4 is to align the primer 3 with a striker 5 only when the conditions of a nominal shot of the projectile are met to prevent accidental initiation of the rocket 1 as explained in the patent. FR2533686 .
  • the striker is oriented so as to be able to translate to the impact of the front AV to the rear AR of the rocket 1 where the primer 3 is located.
  • radial pins 20 blocking the rotor 4 (locked rotor visible at the figure 1 ) are released from the rotor 4 after the unwinding of a hairspring 21 which delays their release so that the unlocking of the rotor 4 occurs only when the projectile has left the barrel of the weapon.
  • the tip of the envelope 2 has a groove 6 whose side walls 2a are constituted by the casing 2 of the rocket 1.
  • the recess 6 has an inlet 8 which opens on the front AV of the rocket 1.
  • This inlet 8 is plugged by a thin cover 11 designed to maintain the aerodynamic performance of the rocket 1 which might otherwise be slightly degraded by the free opening of the inlet 8 of the recess 6.
  • this seal 11 prevents the penetration of debris or unwanted material in the recess 6 during the storage and handling phases of the rocket 1.
  • a bottom 9 which closes the recess 6 in the direction of the interior of the rocket 1.
  • the periphery of the bottom 9 comprises a thinning 9a of its thickness at the zone of connection with the side walls 2a of the recess 6.
  • the bottom 9 of the recess 6 has a cylindrical rear portion 9b which is housed in a bore 10a of a pusher 10 which is itself supported on the striker 5 and in shape correspondence with it at the level of a bowl 10b.
  • the bottom 9 has on its portion delimiting the recess 6 an axial point 9c whose function is to break the cover 11 which upon impact will apply against the bottom 9 on either side of the tip 9c.
  • the matter 101 of the target contained in the recess 6 exerts a pressure on the bottom 9 of the recess following the advance of the rocket 1 in the target 101.
  • the striker 5 strikes the primer 3 which then triggers a pyrotechnic chain (chain not shown) exploding the projectile (projectile not shown) on the surface of the target 101 and no longer in the target as with the rockets of the prior art.
  • the pusher 10 has an enlarged head 10c whose profile is close to the inner surface of the bore of the warhead 2.
  • the shock is applied directly to the striker by the pusher 10 via the deformation of the surface 2.
  • the rocket 1 therefore retains its sensitivity to impact on both hard target and soft target.
  • the inlet 8 will have a diameter D1 smaller than the diameter D2 of the bottom 9.
  • the sand or mud which enters the recess and which contributes to the braking of the projectile behaves like a fluid exerting on the bottom of the recess a pressure which is all the more important that the projectile has a high speed.
  • a given pressure has a shearing effect all the more intense as the surface on which it is exerted is important. It is this phenomenon which explains why a larger diameter at the bottom of the recess facilitates shear failure of the latter and therefore increases the sensitivity of the rocket.
  • the invention therefore makes it possible more particularly to improve the impact sensitivity of the percussion fuzes on soft targets or on soft ground and at a long firing distance (distance greater than or equal to 1000 meters).
  • the breakable nature of the bottom 9 can be obtained by the use of other means of weakening the bottom 9 such as the use of a welded seam at break to join the bottom 9 and the walls 2a for example.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Golf Clubs (AREA)
  • Fuses (AREA)

Claims (6)

  1. Zünder eines Sprengkopfs (1) mit Schlagbolzen (5), wobei der Schlagbolzen (5) ausgerichtet ist, um beim Auftreffen auf ein Ziel eine Zündkapsel (3) des Zünders (1) in Richtung auf die Hinterseite (AR) des Zünders (1) zu schlagen, wobei der Zünder (1) eine Umhüllung (2) umfasst, deren Spitze eine Aushöhlung (6) umfasst, von der ein Eingang (8) offen ist, um die Füllung der Aushöhlung (6) durch das Material des getroffenen Ziels zu gestatten, wobei der Boden (9) der Aushöhlung (6) entlang seinem Umfang aufbrechbar ist und durch den Druck des Materials des Ziels aufgebrochen werden kann, worauf der Boden (9) dann den Schlagbolzen (5) in Richtung auf die Hinterseite (AR) des Zünders (1) schieben kann, dadurch gekennzeichnet, dass der Durchmesser des Eingangs der Aushöhlung (6) geringer als der Durchmesser des Umfangs des Bodens (9) der Aushöhlung (6) ist.
  2. Zünder (1) nach Anspruch 1, dadurch gekennzeichnet, dass der Boden (9) auf Höhe seiner Verbindung (9a) mit der Umhüllung (2) durch eine Verschmälerung seines Umfangs geschwächt ist.
  3. Zünder (1) nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass er einen Schieber (10) zwischen dem Boden (9) und dem Schlagbolzen (5) umfasst, wobei der Schieber (10) dazu bestimmt ist, den Druck des Bodens (9) auf den Schlagbolzen (5) zu übertragen.
  4. Zünder (1) nach Anspruch 3, dadurch gekennzeichnet, dass der Schieber (10) einen erweiterten Kopf (10c) umfasst, dessen Profil nahe an der Innenfläche (2) des Sprengkopfs liegt.
  5. Zünder (1) nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Öffnung der Aushöhlung (6) durch einen Deckel (11) verschlossen ist, der dazu bestimmt ist, die aerodynamischen Merkmale des Sprengkopfs zu optimieren.
  6. Zünder (1) nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der Boden (9) eine axiale Spitze (9c) umfasst, die sich in die Aushöhlung (6) erstreckt.
EP16185058.1A 2015-08-27 2016-08-20 Zünder eines sprengkopfs mit schlagbolzen Active EP3136043B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1501794A FR3040482B1 (fr) 2015-08-27 2015-08-27 Fusee d'ogive a percuteur

Publications (2)

Publication Number Publication Date
EP3136043A1 EP3136043A1 (de) 2017-03-01
EP3136043B1 true EP3136043B1 (de) 2018-12-12

Family

ID=54848614

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16185058.1A Active EP3136043B1 (de) 2015-08-27 2016-08-20 Zünder eines sprengkopfs mit schlagbolzen

Country Status (4)

Country Link
EP (1) EP3136043B1 (de)
ES (1) ES2710510T3 (de)
FR (1) FR3040482B1 (de)
TR (1) TR201903669T4 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113218256A (zh) * 2021-04-16 2021-08-06 南京理工大学 一种具有擦地炸功能的小口径旋转炮弹弹头引信触发机构

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE367014A (de) * 1929-04-29
NL174980B (nl) * 1952-03-17 Rhone Poulenc Ind Reactor, in het bijzonder een heetgasgenerator.
DE1177525B (de) * 1963-07-04 1964-09-03 Diehl Fa Aufschlageinrichtung an Zuendern
US3726228A (en) * 1970-11-23 1973-04-10 Us Army Density integrating fuze head
SE416679B (sv) * 1977-03-02 1981-01-26 Saab Scania Ab Anslagstendror
FR2533686B1 (fr) 1982-09-24 1987-01-02 Manurhin Dispositif de securite a cage tournante pour projectile giratoire
US5243912A (en) 1991-12-09 1993-09-14 General Electric Co. Arming delay, dual environment safe, fuze
FR2796456B1 (fr) * 1999-07-12 2002-09-13 Titan Invest Systeme de declenchement selectif

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
FR3040482A1 (fr) 2017-03-03
EP3136043A1 (de) 2017-03-01
FR3040482B1 (fr) 2018-02-16
TR201903669T4 (tr) 2019-04-22
ES2710510T3 (es) 2019-04-25

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