EP0236553A1 - Ogive déployable pour charges creuses - Google Patents

Ogive déployable pour charges creuses Download PDF

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Publication number
EP0236553A1
EP0236553A1 EP86115868A EP86115868A EP0236553A1 EP 0236553 A1 EP0236553 A1 EP 0236553A1 EP 86115868 A EP86115868 A EP 86115868A EP 86115868 A EP86115868 A EP 86115868A EP 0236553 A1 EP0236553 A1 EP 0236553A1
Authority
EP
European Patent Office
Prior art keywords
ignition
charge
contact
extended
mandrel
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
EP86115868A
Other languages
German (de)
English (en)
Other versions
EP0236553B1 (fr
Inventor
Hans Spengler
Klaus Peter Geiss
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of EP0236553A1 publication Critical patent/EP0236553A1/fr
Application granted granted Critical
Publication of EP0236553B1 publication Critical patent/EP0236553B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge
    • F42B12/105—Protruding target distance or stand-off members therefor, e.g. slidably mounted
    • 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
    • F42C1/14—Impact fuzes, i.e. fuzes actuated only by ammunition impact operating at a predetermined distance from ground or target by means of a protruding member

Definitions

  • the invention relates to a device for extending the impact contact for shaped charges for triggering ignition, which is stored in the rest position in the recess of the shaped charge, wherein the spacer mandrel carrying it can be locked for a selectable distance and the ignition circuit is closed for the detonator.
  • the present invention is based on this and has set itself the task of improving this device in such a way that the sting formation space is free from combustion residues, pressurization and temperature effects when the spacer mandrel is extended.
  • This exemplary embodiment is also based on the idea of combining the current pulse of a piezo ignition 33 with a propellant charge 32 in order to variably extend the spacer mandrel 34 of a shaped charge.
  • the embodiment of a hollow charge 30 shown in the figure has a spacing mandrel 34 mounted in its free space 30a.
  • This spacing mandrel is guided in the hood 30b of the shaped charge floor 30 and is fixed on the one hand by a shear pin 36 and on the other hand by an anti-rotation pin 36a.
  • At the top of this spacer mandrel 34 there is a piezo ignition 33 for the propellant charge 32 and a piezo generator 31 for the main hollow charge or the secondary hollow charge 39.
  • diagonally directed nozzles 35 are arranged at the front end of the spacer mandrel 34.
  • the latter is provided at its rear end, which is mounted in the free space 30a, with an electrical contact plug 37a, which comes to an enlarged size in a contact socket 37b in the extended mandrel position and is thus connected to the detonator of the shaped charge 30 via the ignition line 37c.
  • the above-described device functions as follows: The tube movement 40 of the launch tube 38 is ejected by the launching movement of the missile and the piezo ignition 33 for the propellant charge 32 is thereby activated. Ignition device 33 and propellant charge 32 are arranged outside the spike formation space 30a. Due to the recoil of this propellant charge 32 via the rearward-directed nozzles 35, the spacer mandrel 34, which can be designed as a telescope, is brought into the respectively specified extended position "x". It should also be mentioned that in order to ensure adequate safety in the front pipe, the ignition pulse of the piezo ignition 33, the propellant charge 32 is to be activated with a time delay after the rocket engine ignition.
  • the electrical plug 37a arranged at its rear end comes into the closed position with the contact socket 37b arranged on the projectile hood 30b and automatically establishes the electrical ignition connection to the shaped charge via the ignition line 37c.
  • the impact contact 33a when it strikes the line, fires the shaped charge stack 30 in a known manner via the piezo ignition 31.
  • the cavity of the spacer mandrel 34 either receive a precharge charge or secondary charge 39 which is in electrical connection with the plug elements 37a and 37b or that sensors, trim weights etc. are accommodated in the cavity. These elements are also mounted in such a way that they come to rest outside the spike formation space when extended.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Air Bags (AREA)
  • Automotive Seat Belt Assembly (AREA)
EP19860115868 1986-01-16 1986-11-14 Ogive déployable pour charges creuses Expired - Lifetime EP0236553B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3601052 1986-01-16
DE3601052 1986-01-16

Publications (2)

Publication Number Publication Date
EP0236553A1 true EP0236553A1 (fr) 1987-09-16
EP0236553B1 EP0236553B1 (fr) 1990-02-28

Family

ID=6291923

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19860115868 Expired - Lifetime EP0236553B1 (fr) 1986-01-16 1986-11-14 Ogive déployable pour charges creuses

Country Status (1)

Country Link
EP (1) EP0236553B1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0409441A2 (fr) * 1989-07-19 1991-01-23 Hughes Aircraft Company Dispositif modulaire de perfectionnement pour missiles
US5229113A (en) * 1987-04-07 1993-07-20 Lubrizol Genetics, Inc. Bradyrhizobium japonicum nodulation inducing factor

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE9100116U1 (de) * 1991-01-07 1991-06-06 Josef Lubig GmbH, 5300 Bonn Exerziergranate
PL234192B1 (pl) * 2017-11-09 2020-01-31 Zakl Metalowe Dezamet Spolka Akcyjna Zapalnik elektroniczny programowalny, zwłaszcza do nabojów granatnikowych i układ zasilająco-sterujący zapalnika elektronicznego programowalnego, zwłaszcza do nabojów granatnikowych

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1935724A1 (de) * 1968-08-22 1970-03-12 Oerlikon Buehrle Ag Hohlladungsgeschoss
FR2310547A1 (fr) * 1975-05-06 1976-12-03 Realisa Et Applic Tech Et Perfectionnements aux charges creuses
FR2539505A1 (fr) * 1983-01-14 1984-07-20 Luchaire Sa Ogive perfectionnee pour projectile

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1935724A1 (de) * 1968-08-22 1970-03-12 Oerlikon Buehrle Ag Hohlladungsgeschoss
FR2310547A1 (fr) * 1975-05-06 1976-12-03 Realisa Et Applic Tech Et Perfectionnements aux charges creuses
FR2539505A1 (fr) * 1983-01-14 1984-07-20 Luchaire Sa Ogive perfectionnee pour projectile

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5229113A (en) * 1987-04-07 1993-07-20 Lubrizol Genetics, Inc. Bradyrhizobium japonicum nodulation inducing factor
EP0409441A2 (fr) * 1989-07-19 1991-01-23 Hughes Aircraft Company Dispositif modulaire de perfectionnement pour missiles
EP0409441A3 (en) * 1989-07-19 1992-03-25 Hughes Aircraft Company Modular missile upgrade apparatus

Also Published As

Publication number Publication date
EP0236553B1 (fr) 1990-02-28

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