EP0236553B1 - Ogive déployable pour charges creuses - Google Patents

Ogive déployable pour charges creuses Download PDF

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Publication number
EP0236553B1
EP0236553B1 EP19860115868 EP86115868A EP0236553B1 EP 0236553 B1 EP0236553 B1 EP 0236553B1 EP 19860115868 EP19860115868 EP 19860115868 EP 86115868 A EP86115868 A EP 86115868A EP 0236553 B1 EP0236553 B1 EP 0236553B1
Authority
EP
European Patent Office
Prior art keywords
ignition
charge
mandrel
spacing mandrel
extended
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.)
Expired - Lifetime
Application number
EP19860115868
Other languages
German (de)
English (en)
Other versions
EP0236553A1 (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 of rocket projectiles for triggering the ignition, which is stored in the rest position in the recess of the shaped charge, the spacer mandrel carrying it extended lockable by a selectable distance and the ignition circuit for the detonator is closed.
  • a device for extending the impact contact for shaped charges of rocket projectiles for triggering the ignition which is stored in the rest position in the recess of the shaped charge, the spacer mandrel carrying it extended lockable by a selectable distance and the ignition circuit for the detonator is closed.
  • Such a device is known from FR-A 2 539 505 and has also been developed in one embodiment by the applicant and has proven itself. From FR-A 2 310 547 it has also become known to extend a spacer mandrel by means of pyrotechnic means.
  • the present invention is based on the first-mentioned embodiments and has set itself the task of improving the device in such a way that the sting formation space becomes 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 shaped 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 projectile 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 spacing mandrel 34, which can be designed as a telescope, is brought into the respectively predetermined 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 charge 33a when it strikes the line causes the shaped charge projectile 30 to be ignited in a known manner via the piezo ignition 31.
  • the cavity of the spacer mandrel 34 either receive a precharge or side cavity 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)
  • Automotive Seat Belt Assembly (AREA)
  • Air Bags (AREA)

Claims (4)

1. Dispositif pour déployer le contact à impact (33a) pour des charges creuses (30) de fusées balistiques afin de déclencher l'amorçage, ledit contact étant logé en position de repos dans l'évidement (30a) de la charge creuse (30), la broche d'espacement (34) qui le porte étant déployée sur une distance choisie et bloquée et le circuit d'amorçage pour le détonateur étant fermé, caractérisé en ce qu'une charge propulsive (32) est disposée à l'extrémité avant de la broche d'espacement (34) munie du contact à impact (33a), à 1, extérieur de 1, espace de formation du dard, et en ce que cette charge propulsive (32) est amorcée automatiquement par l'intermédiaire d'un piézogénérateur (31) par l'accélération de lancement de la tête de combat et la broche d'espacement (34) est déployée par le recul de tuyères (35) orientées dans la direction de vol en biais vers l'arrière à l'extrémité avant de la broche d'espacement .
2. Dispositif selon la revendication 1, caractérisé en ce que l'amorçage de la charge propulsive (32) s'effectue par l'impulsion d'amorçage apparaissant lors de l'éjections d'un couvercle de tube (40) en retard après l'allumage du moteur-fusée.
3. Dispositif selon la revendication 1, caractérisée en ce qu'une fiche de contact (37a) qui, dans la position déployée, coopère avec une douille de contact (37b), est disposée dans la direction de vol à l'extrémité arrière de la broche d'espacement (34) déployable.
4. Dispositif selon une ou plusieurs des revendications 1 à 3, caractérisé en ce que la broche d'espacement (34) est réalisée en tant que support pour un détecteur, une précharge creuse antérieure ou un poids d'équilibrage (39).
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 EP0236553A1 (fr) 1987-09-16
EP0236553B1 true 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
DE9100116U1 (de) * 1991-01-07 1991-06-06 Josef Lubig GmbH, 5300 Bonn Exerziergranate
PL423398A1 (pl) * 2017-11-09 2019-05-20 Zakl Metalowe Dezamet Spolka Akcyjna Zapalnik elektroniczny programowalny, zwłaszcza do nabojów granatnikowych i układ zasilająco-sterujący zapalnika elektronicznego programowalnego, zwłaszcza do nabojów granatnikowych

Families Citing this family (2)

* 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
US5007347A (en) * 1989-07-19 1991-04-16 Hughes Aircraft Company Modular missile upgrade apparatus

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH495545A (de) * 1968-08-22 1970-08-31 Oerlikon Buehrle Ag Hohlladungsgeschoss
FR2310547A1 (fr) * 1975-05-06 1976-12-03 Realisa Et Applic Tech Et Perfectionnements aux charges creuses
FR2539505B1 (fr) * 1983-01-14 1987-07-17 Luchaire Sa Ogive perfectionnee pour projectile

Cited By (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
PL423398A1 (pl) * 2017-11-09 2019-05-20 Zakl Metalowe Dezamet Spolka Akcyjna Zapalnik elektroniczny programowalny, zwłaszcza do nabojów granatnikowych i układ zasilająco-sterujący zapalnika elektronicznego programowalnego, zwłaszcza do nabojów granatnikowych

Also Published As

Publication number Publication date
EP0236553A1 (fr) 1987-09-16

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