EP3924686B1 - Rakete für ein geschoss zur abfeuerung durch eine kanone - Google Patents

Rakete für ein geschoss zur abfeuerung durch eine kanone

Info

Publication number
EP3924686B1
EP3924686B1 EP20710273.2A EP20710273A EP3924686B1 EP 3924686 B1 EP3924686 B1 EP 3924686B1 EP 20710273 A EP20710273 A EP 20710273A EP 3924686 B1 EP3924686 B1 EP 3924686B1
Authority
EP
European Patent Office
Prior art keywords
fuze
capacitor
charge
fire
arming
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
EP20710273.2A
Other languages
English (en)
French (fr)
Other versions
EP3924686A1 (de
Inventor
Jean Luc PERON
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
KNDS Ammo France 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 KNDS Ammo France SA filed Critical KNDS Ammo France SA
Publication of EP3924686A1 publication Critical patent/EP3924686A1/de
Application granted granted Critical
Publication of EP3924686B1 publication Critical patent/EP3924686B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/58—Electric firing mechanisms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C11/00—Electric fuzes
    • F42C11/008—Power generation in electric fuzes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/005—Combination-type safety mechanisms, i.e. two or more safeties are moved in a predetermined sequence to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/40—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected electrically

Definitions

  • rocket according to the invention is particularly well suited to the definition of rockets for projectiles and munitions which can be fired by smooth tubes.
  • the invention also relates to a munition equipped with such a rocket and a method of arming such a rocket.
  • the invention relates to a fuse for a projectile intended to be fired by a cannon by the ignition of a propellant charge by an electrical ignition means, such as an electrical igniter, a fuse capable of passing from a safety position to an armed position, following firing, by the lifting of at least two different safeties, such that the fuse comprises a capacitor which is intended to be connected to the electrical ignition means of the propellant charge and which charges when said propellant charge is ignited, said fuse also comprises a computer which detects the charge of the capacitor to allow the arming of the fuse when this charge is greater than or equal to a reference value, the charge of the capacitor constituting a first firing safety.
  • an electrical ignition means such as an electrical igniter
  • a fuse capable of passing from a safety position to an armed position, following firing, by the lifting of at least two different safeties
  • the fuse comprises a capacitor which is intended to be connected to the electrical ignition means of the propellant charge and which charges when said propellant charge is ignited
  • said fuse also comprises a computer which detects the
  • the rocket may include an electric generator which is initiated by inertia when fired.
  • the rocket may include an inertial sensor which is connected to the computer and which constitutes a second firing safety.
  • the rocket may have a divider bridge between the electric ignition means and the capacitor.
  • the rocket capacitor may be arranged between the gate and the source of a field effect transistor, the drain of this capacitor being powered by the electric generator and being connected to a logic module of the computer, the source also being connected to a ground of the rocket, the threshold voltage V GS of the transistor constituting the reference value.
  • the invention also relates to ammunition which is intended to be fired by a cannon and comprising a projectile and a propellant charge equipped with an electrical ignition means, such as an electrical igniter, fixed to a base, the projectile comprising a fuse according to the preceding characteristics and a wire connection connecting the fuse to the igniter.
  • an electrical ignition means such as an electrical igniter
  • the ammunition may include a divider bridge between the electrical ignition means and the capacitor, a divider bridge which is housed in the base.
  • the firing acceleration as a second event associated with the firing and allowing the rocket to be armed.
  • an electric generator is used which is initiated by inertia during firing, the activation of the generator ensuring the electrical power supply to the rocket.
  • a munition 1 according to the invention is intended to be fired by a cannon (not shown), for example a cannon of caliber greater than or equal to 40mm, such as a 120mm tank cannon.
  • the projectile 2 is fixed to the socket 4 at a front connecting piece 8 and it is equipped with a sealing belt 9.
  • the patent EP307307 describes an example of a connecting part between a projectile and a combustible case.
  • the projectile 2 carries at its rear part a deployable tail 10, pivotally mounted on axes integral with a tail 11.
  • Projectile 2 is for example an explosive projectile whose metallic body contains an explosive material (not shown).
  • the explosive material is capable of being initiated by a fuse 11 (shown in dotted lines) which is housed in a base 2a of projectile 2.
  • the rocket 11 could also be a programmable rocket. It would therefore be possible to associate the wired connection 12 connected to the igniter 6 with another wired connection (not visible Figure 1 ) which will be connected to a contact pad on the base allowing programming signals to be introduced from the rocket 11 before firing.
  • the calculator 18 will measure the charge level of the capacitor 20, for example by comparison with a reference value stored in memory, or more simply by switching a static relay whose switching level (reference value) is set by an electronic circuit (incorporated into the fuse 11) to a level corresponding to the minimum discharge current of the capacitor 20 which is expected.
  • the safety and arming device 13 of the rocket 11 can therefore only move from a safety position to an armed position following the lifting of two different safeties: the detection of the ignition current of the propellant charge and the detection of the longitudinal firing acceleration.
  • the firing safety is then ensured by the fuse 11 itself, which can only control the slapper after the two firing safeties have been lifted.
  • the firing safeties will be logic locks independent of each other and which must be distinct from the firing chain itself.
  • the divider bridge 23, even if it is functionally part of the fuse 11, is structurally arranged at the base 5. Thus the current passing in the wire connection 12 is reduced.
  • the capacitor 20 is powered through a load resistor R 3 , another resistor R 4 is connected in parallel between the terminals of the capacitor 20.
  • the purpose of the resistor R 4 is to allow the discharge of the capacitor 20, after detection of its charged state by the computer 18, during the flight of the projectile. It thus allows the evacuation of parasitic charges which could disturb the operation of the rocket.
  • R 3 and the capacitor 20 in fact form a low-pass filter making it possible to eliminate parasitic high frequencies
  • the firing of the igniter 6 ignites the propellant charge, therefore causes the capacitor 20 to charge.
  • the MOS transistor 24 closes and the current coming from the generator 19 is discharged to the ground 28 via the connection 29. This results in a voltage close to 0 volts applied to the logic module 27 of the computer via the connection 26.
  • the load resistor R 5 makes it possible to avoid short-circuiting the generator 19.
  • the logic module 27 detects the firing acceleration seen by the accelerometer 22.
  • the rocket 11, and more particularly the firing management module 30, also receives, as described previously, the wired connection 21 allowing the programming of the desired operating mode for the rocket.
  • the invention is more particularly suited to ammunition fired from a smooth-bore weapon tube. It is clear, however, that it can also be implemented with ammunition fired from a rifled tube.
  • the firing event associated with the ignition of the propellant charge can then be combined with either axial acceleration of the projectile or rotational acceleration.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Automotive Seat Belt Assembly (AREA)

Claims (10)

  1. - Raketenantrieb (11) für ein Geschoss, das dazu bestimmt ist, von einer Kanone durch Zünden einer Treibladung (3) durch eine elektrisches Zündeinrichtung (6), wie beispielsweise einen elektrischen Zünder (6), abgefeuert zu werden, wobei der Raketenantrieb (11) nach Abfeuern durch Aufheben von mindestens zwei verschiedenen Sicherungen von einer gesicherten in eine scharfgestellte Stellung übergehen kann, der Raketenantrieb umfassend einen Kondensator (20), der dazu bestimmt ist, mit der elektrischen Zündeinrichtung (6) der Treibladung (3) verbunden zu werden, dadurch gekennzeichnet, dass sich der Kondensator bei Zündung der Treibladung auflädt, der Raketenantrieb auch umfassend einen Rechner (18), der die Ladung des Kondensators (20) erfasst, um das Scharfstellen des Raketenantriebs (11) zu ermöglichen, wenn diese Ladung größer als oder gleich wie ein Referenzwert ist, wobei die Ladung des Kondensators (20) eine erste Abschusssicherung darstellt.
  2. - Raketenantrieb nach Anspruch 1, dadurch gekennzeichnet, dass er einen elektrischen Generator (19) umfasst, der beim Abschießen durch Trägheit gezündet wird.
  3. - Raketenantrieb nach Anspruch 1, dadurch gekennzeichnet, dass er einen Trägheitssensor (22) umfasst, der mit dem Rechner (18) verbunden ist und eine zweite Abschusssicherung darstellt.
  4. - Raketenantrieb nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass er eine Teilerbrücke (23) zwischen der elektrischen Zündeinrichtung (6) und dem Kondensator (20) umfasst.
  5. - Raketenantrieb nach den Ansprüchen 2 und 4, dadurch gekennzeichnet, dass der Kondensator (20) zwischen dem Gate G und der Source D eines Feldeffekttransistors (24) angeordnet ist, wobei der Drain D dieses Kondensators von dem elektrischen Generator (19) gespeist wird und mit einem Logikmodul (27) des Rechners (18) verbunden ist, wobei die Source S auch mit einer Masse des Raketenantriebs verbunden ist, die Schwellenspannung VGS des Transistors (24) den Referenzwert darstellt.
  6. - Munition (1), die dazu bestimmt ist, von einer Kanone abgefeuert zu werden, und die ein Projektil (2) und eine Treibladung (3) umfasst, die mit einer elektrischen Zündeinrichtung (6), wie beispielsweise einem elektrischen Zünder (6), ausgestattet ist, der an einer Bodenkappe (5) befestigt ist, das Geschoss (1) umfassend einen Raketenantrieb (11) nach einem der Ansprüche 1 bis 5, wobei eine verdrahtete Verbindung (12) den Zünder (11) mit dem Zünder (6) verbindet.
  7. - Munition nach Anspruch 6, dadurch gekennzeichnet, dass sie eine Teilerbrücke (23) zwischen der elektrischen Zündeinrichtung (6) und dem Kondensator (20) aufweist, wobei die Teilerbrücke (23) in der Bodenkappe (5) untergebracht ist.
  8. - Verfahren zum Scharfstellen eines Raketenantriebs (11), mit dem ein Geschoss (1) beim Abfeuern durch eine Kanone ausgerüstet ist, Verfahren, bei dem der Schuss durch das Erkennen von mindestens zwei verschiedenen Ereignissen, die üblicherweise mit einem Schuss assoziiert sind, erkannt wird, wobei es die Kombination der zwei Ereignisse ermöglicht, den Raketenantrieb (11) scharfzustellen, wobei das Verfahren durch die folgenden Schritte gekennzeichnet ist:
    - Laden eines Kondensators (20) des Raketenantriebs (11) anhand eines Signals zum Zünden einer Treibladung (3),
    - Verwenden der Ladung des Kondensators (20) als ein erstes Ereignis, das mit dem Abschuss assoziiert ist und das Scharfstellen des Raketenantriebs (11) ermöglicht, einen Rechner (18), der die Ladung des Kondensators (20) erfasst, um das Scharfstellen des Raketenantriebs (11) zu ermöglichen, wenn diese Ladung größer als oder gleich wie ein Referenzwert ist.
  9. - Verfahren zum Scharfstellen eines Raketenantriebs nach Anspruch 8, wobei bei dem Verfahren die Beschleunigung des Abschusses als zweites Ereignis verwendet wird, das mit dem Abschuss assoziiert ist und das Scharfstellen des Raketenantriebs (11) ermöglicht.
  10. - Verfahren zum Scharfstellen eines Raketenantriebs nach einem der Ansprüche 8 oder 9, wobei bei dem Verfahren ein elektrischer Generator (19) eingesetzt wird, der beim Abschuss durch Trägheit gezündet wird, wobei das Einschalten des Generators (19) die Stromversorgung des Raketenantriebs (11) sicherstellt.
EP20710273.2A 2019-02-13 2020-02-06 Rakete für ein geschoss zur abfeuerung durch eine kanone Active EP3924686B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1901348A FR3092660B1 (fr) 2019-02-13 2019-02-13 Fusee pour un projectile destine a etre tire par un canon
PCT/IB2020/050945 WO2020165699A1 (fr) 2019-02-13 2020-02-06 Fusee pour un projectile destine a etre tire par un canon

Publications (2)

Publication Number Publication Date
EP3924686A1 EP3924686A1 (de) 2021-12-22
EP3924686B1 true EP3924686B1 (de) 2025-07-23

Family

ID=67262544

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20710273.2A Active EP3924686B1 (de) 2019-02-13 2020-02-06 Rakete für ein geschoss zur abfeuerung durch eine kanone

Country Status (5)

Country Link
US (1) US11774225B2 (de)
EP (1) EP3924686B1 (de)
FR (1) FR3092660B1 (de)
IL (1) IL285468B1 (de)
WO (1) WO2020165699A1 (de)

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3739726A (en) * 1970-08-17 1973-06-19 Intron Int Inc Electronic fuze
DE2059665C3 (de) * 1970-12-04 1978-04-20 Rheinmetall Gmbh, 4000 Duesseldorf Verfahren und Anordnung zur Berücksichtigung von Munitionseigenschaften beim Richten eines Geschützes und/ oder beim Einstellen des Zünders der Munition
US4015531A (en) * 1975-01-31 1977-04-05 General Electric Company Electrical fuze with selectable modes of operation
FR2620214B1 (fr) 1987-09-09 1990-04-13 France Etat Armement Bague de liaison entre un projectile et une douille
FR2633385B1 (fr) 1988-06-23 1990-08-31 France Etat Armement Systeme de securite et d'armement pour projectile utilisant la pression des gaz de combustion
US5097765A (en) * 1991-03-28 1992-03-24 The United States Of America As Represented By The Secretary Of The Army Electric fuze with selectable modes
US5458995A (en) 1994-08-12 1995-10-17 The United States Of America As Represented By The Secretary Of The Army Solid state electrochemical cell including lithium iodide as an electrolyte additive
FR2802297B1 (fr) 1999-12-08 2002-10-11 Giat Ind Sa Tube allumeur pour munition d'artillerie
DE10038066B4 (de) 2000-08-04 2004-07-08 Junghans Feinwerktechnik Gmbh & Co. Kg Aktivierbare Batterie für einen elektronischen Artilleriezünder
FR2824898B1 (fr) 2001-05-18 2003-09-12 Giat Ind Sa Culot pour munition destine a recevoir un allumeur electrique
DE20115732U1 (de) 2001-09-25 2001-12-06 Bruckbauer & Pral Ges. M.B.H., Salzburg Halteeinrichtung
US6951161B2 (en) 2003-12-17 2005-10-04 Alliant Techsystems, Inc. Smooth bore second environment sensing
US7504177B2 (en) 2004-08-23 2009-03-17 Eaglepicher Technologies, Llc Reserve battery with set back mechanism for delayed battery activation
DE102006047549B4 (de) 2006-10-07 2010-04-22 Junghans Microtec Gmbh Zünder für ein drallfreies Geschoss
US8677900B2 (en) * 2007-07-10 2014-03-25 Omnitek Partners Llc Inertially operated electrical initiation devices
FR2930026B1 (fr) 2008-04-09 2010-05-07 Nexter Munitions Munition de gros calibre chargee par l'arriere
US8603658B2 (en) 2010-04-16 2013-12-10 Eaglepicher Technologies, Llc Activation mechanism for a reserve battery cell
US10062910B2 (en) 2010-05-27 2018-08-28 Omnitek Partners Llc Reserve power source for munitions
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US10468689B2 (en) 2015-10-20 2019-11-05 Eaglepicher Technologies, Llc Thermal battery and methods of activation

Also Published As

Publication number Publication date
FR3092660A1 (fr) 2020-08-14
US20220357140A1 (en) 2022-11-10
IL285468A (en) 2021-09-30
IL285468B1 (en) 2025-12-01
US11774225B2 (en) 2023-10-03
WO2020165699A1 (fr) 2020-08-20
FR3092660B1 (fr) 2022-04-01
EP3924686A1 (de) 2021-12-22

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