[go: up one dir, main page]

EP0236325B1 - Detonateur auto-destructeur - Google Patents

Detonateur auto-destructeur Download PDF

Info

Publication number
EP0236325B1
EP0236325B1 EP85905808A EP85905808A EP0236325B1 EP 0236325 B1 EP0236325 B1 EP 0236325B1 EP 85905808 A EP85905808 A EP 85905808A EP 85905808 A EP85905808 A EP 85905808A EP 0236325 B1 EP0236325 B1 EP 0236325B1
Authority
EP
European Patent Office
Prior art keywords
warhead
detonator
needle
igniter
detonating needle
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
Application number
EP85905808A
Other languages
German (de)
English (en)
Other versions
EP0236325A1 (fr
Inventor
Karl-Heinz Roosmann
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Priority to AT85905808T priority Critical patent/ATE48310T1/de
Publication of EP0236325A1 publication Critical patent/EP0236325A1/fr
Application granted granted Critical
Publication of EP0236325B1 publication Critical patent/EP0236325B1/fr
Expired legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C9/00—Time fuzes; Combined time and percussion or pressure-actuated fuzes; Fuzes for timed self-destruction of ammunition
    • F42C9/14—Double fuzes; Multiple fuzes
    • F42C9/142—Double fuzes; Multiple fuzes combined time and percussion fuzes in which the timing is caused by combustion

Definitions

  • the invention relates to a warhead according to the preamble of claim 1.
  • Such a warhead is known from DE-A-2 242 930.
  • the known warhead comprises a warhead housing for receiving a shaped charge as well as an impact detonator connected to the warhead housing and comprising a firing pin movably mounted in the axial direction.
  • the warhead is transported in large numbers by a missile or carrier projectile over a target area and is ejected there.
  • the firing pin accelerates due to its inertia and ignites a displaceable detonator, which in turn detonates the charge of the warhead, preferably a shaped charge.
  • the invention is based, to expand this known warhead by a self-disassembly the task.
  • DE-B-1 101 225 discloses an ogive-shaped impact detonator with a self-dismantling device arranged on the tip side in a large-caliber swirl-stabilized artillery projectile.
  • the known detonator arrangement functions according to a completely different principle of operation: When fired from the barrel weapon, a delay charge is to be ignited by a primer set that can be displaced in the hollow firing needle / hammer against the force of a compression spring. After acceleration in the tube, the primer is immediately separated from the deceleration charge by the compression spring; reliable ignition cannot therefore be guaranteed.
  • the hollow firing pin contains many other components, which makes it very long and makes it impossible to use it in a much smaller warhead (bomblet).
  • the firing pin of this known artillery projectile does not act against the flight direction due to inertia; In order for it to be effective, the projectile must be deformed on the tip side to such an extent that the hollow cylindrical impact body is hammered into the detonator with the firing needle to the rear.
  • the projectile tip is deformed and ignition does not occur.
  • the projectile is also e.g. not deformed and ignited on the tip side in snow or soft ground or with a very flat target impact. Due to the undefined distance of the firing needle or the impact body to the detonator carrier or the detonator charge, a reliably functioning self-decomposition via the retarding primer or the self-decomposing primer is highly doubtful.
  • the detonator housing is arranged on the rear side, both ignition needles point in the direction of flight, the second ignition needle for the retarding primer is arranged in a fixed position, while the first ignition needle is driven into the detonator charge without interference by its inertia on target impact.
  • safe ignition and self-decomposition are ensured due to the low overall height and the short distances between the output primer and the detonator charge.
  • the invention offers the advantage that the own troops, possibly endangering unexploded ordnance, are largely avoided, since the self-destruct device activates the warhead of the warhead even in the event of a failure of the impact detonator and thus renders it harmless. In addition, however, this increases the reliability of the warhead, since even if the impact detonator fails, the self-disassembly device can still detonate the warfare and thus make the warhead effective.
  • Fig. 1 shows a schematic representation of a warhead 10 in side view.
  • the warhead 10 comprises a warhead housing 11 for receiving a war charge, preferably a shaped charge.
  • a detonator housing 12 arranged at the rear is connected, which contains an impact detonator.
  • a swirl brake 13 is attached to the detonator housing and, after the warhead 10 has been ejected from the spin-stabilized carrier projectile, reduces the number of swirls and improves the flight stability of the warhead 10 when it descends to the target area.
  • the impact detonator (FIG. 2) comprises an ignition needle 1, which is fixed in the secured position, but is axially movable in the unlocked state and interacts with a detonator 8 which, if necessary, detonates the combat charge 10 by means of a transfer charge 9.
  • the firing needle 1 is hollow and has a tapping primer 1 a, a pyrotechnic delay line 1 b, and an output primer 1 c in its recess in the following row, starting at the rear.
  • a needle 7, which cooperates with the tapping primer 1 a, is also arranged in a fixed position in the igniter housing 12.
  • the mode of operation of the self-disassembling and ignition device is as follows:
  • the starting point is the safeguard shown in FIG. 2, in which the ignition needle 1 is displaceable in the radial direction like trained securing means 5 is fixed and therefore can not move in the axial direction even when subjected to impact.
  • the tip 1b of the firing needle 1 lies in a blind bore of the detonator carrier 8c, which is acted upon by a compression spring 8d and can be extended in the radial direction, and thereby prevents its evasion in the radial direction.
  • the compression spring 6 acting in the axial direction pushes the ignition needle 1 backwards, the needle 7 fixed to the housing activating the tapping primer 1 a, which in turn activates the pyrotechnic delay line 1 b.
  • the tip 1 d has slipped out of the blind bore 8b and has released the detonator carrier 8c, which now swings spring-loaded in the radial direction in such a way that the detonator 8 comes to rest under the tip 1 d of the firing needle 1 and thereby aligns with the transfer charge 9 and thus produces a pyrotechnic ignition chain for combat charge 10.
  • the tip 1 d of the firing needle 1 is in the ready-to-fire position above the detonator 8 up to the target impact of the warhead.
  • the firing needle 1 due to its inertia, accelerates against the force of the compression spring 6 in the axial direction and pricks the detonator 8, which in turn mediates the transfer charge 9 detonates the combat charge 10.
  • the self-disassembly device also acts.
  • the pyrotechnic delay line 1 has been blown to the output ignition charge 1 and activates it, as a result of which a flame front passes through the bores 1e in the area of the needle 1 and acts upon the erroneously not activated detonator 8 with such a high temperature that it still operates .
  • the self-disassembly device will still ensure that even if the main firing chain fails, the battle charge 1 Oa detonates in time and the warhead 10 is therefore intended to be effective.
  • the output primer 1 c is advantageously designed to be detonative, as a result of which even greater security for activating the combat charge 10 a can be achieved.
  • the burning time of the pyrotechnic delay line 1 b was dimensioned to be about 8-10 seconds.
  • the pyrotechnic delay line consisted of a known pyrotechnic composition with a diameter of approximately 3 mm and an envelope with a thickness of approximately 1.5 mm; the entire length of the pyrotechnic delay line was approximately 18 mm.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Ceramic Products (AREA)

Abstract

Une tête explosive comprend un bâti pour recevoir une charge explosive et un bâti détonateur, connecté au premier bâti, dans lequel est agencé un détonateur à percussion. Le détonateur à percussion comprend un percuteur (1) qui coopère avec un détonateur (8). Afin d'obtenir un effet d'auto-destruction, le percuteur (1) est creux et comprend, agencés d'arrière en avant dans un évidement, une composition détonatrice d'amorçage (1a), un élément pyrotechnique de retardement (1b) et une composition détonatrice de sortie (1c). Un percuteur (7) est agencé de façon fixe dans le bâti détonateur (12) de façon à coopérer avec la composition détonatrice d'amorçage (1a). Lors d'une défaillance du détonateur (8) percuté par la pointe (1d) en frappant la cible, la composition détonatrice de sortie (1c) est activée à travers l'élément pyrotechnique de retardement (1b), après l'amorçage de la composition détonatrice d'amorçage (1a) par le percuteur (7), ce qui fait détoner le détonateur (8) défaillant et finalement active la charge explosive (10a) par l'intermédiaire de la charge de transmission (9).

Claims (3)

1. Tête de combat, à transporter en assez grand nombre par un missile ou un projectile vecteur duquel il est éjecté au-dessus d'une zone de cible, comportant un boîtier de tête de combat (11) pour loger une charge offensive (10a), en particulier une charge creuse, et un boîtier de fusée d'amorçage (12) placée vers l'arrière sur la tête de combat (10), contenant un détonateur à percussion qui comprend lui- même un premier percuteur (1) mobile suivant l'axe longitudinal, coopérant avec un détonateur (8) mobile transversalement, caractérisée par les caractéristiques suivantes;
le premier percuteur (1) est de conformation creuse et dans son évidement sont disposés dans l'ordre suivant à partir de l'arrière, une composition d'amorçage (1a), un relais à retard pyrotechnique (1b) et une composition d'allumage de sortie (1c)
dans le boîtier de fusée (12), est disposé sur la face intérieure de la paroi frontale de terminaison postérieure, en position fixe, un second percuteur (7) coopérant avec la composition d'amorçage (1a),
le premier percuteur (1) est, après expulsion du projectile vecteur et après libération par des moyens de sûreté (5) sous l'action de la force élastique d'un ressort de compression (6), disposé coaxialement autour du premier percuteur (1) dans le boîtier de fusée (12), mobile axialement vers l'arrière et peut ainsi être activé par la composition d'amorçage (1 a),
le premier percuteur (1) et le second percuteur (7) sont dirigés dans le sens de propagation de la tête de combat (10) et
le premier percuteur (1) est conformé de façon à pouvoir se déplacer en direction axiale vers le détonateur (8), contre la force du ressort de compression (6), lors de l'impact sur la cible, en raison de son inertie.
2. Tête de combat selon la revendication 1, caractérisée par le fait que dans la zone de la pointe (1d) du percuteur (1) sont disposées des ouvertures (1e) pour le passage des flammes.
3. Tête de combat selon l'une quelconque des revendications 1 et 2, caractérisée par le fait que la composition d'amorçage de sortie (1c) est détona- trice.
EP85905808A 1984-12-19 1985-11-07 Detonateur auto-destructeur Expired EP0236325B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT85905808T ATE48310T1 (de) 1984-12-19 1985-11-07 Selbstzerlegerzuender.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843446314 DE3446314A1 (de) 1984-12-19 1984-12-19 Gefechtskopf
DE3446314 1984-12-19

Publications (2)

Publication Number Publication Date
EP0236325A1 EP0236325A1 (fr) 1987-09-16
EP0236325B1 true EP0236325B1 (fr) 1989-11-29

Family

ID=6253203

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85905808A Expired EP0236325B1 (fr) 1984-12-19 1985-11-07 Detonateur auto-destructeur

Country Status (5)

Country Link
US (1) US4736682A (fr)
EP (1) EP0236325B1 (fr)
DE (2) DE3446314A1 (fr)
NO (1) NO863090L (fr)
WO (1) WO1986003828A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5105742A (en) * 1990-03-15 1992-04-21 Sumner Cyril R Fluid sensitive, polarity sensitive safety detonator
ES2067355B1 (es) * 1992-03-23 1998-05-01 Garcia Garcia Jose Granada de mano de accion total.
DE4335022C2 (de) * 1993-10-14 1998-06-10 Rheinmetall Ind Ag Zünd- und Sicherungseinrichtung mit Selbstzerlegungseinrichtung für ein mit einer Hohlladungseinlage versehenes Granatengeschoß
FR2959303B1 (fr) * 2010-04-27 2012-04-06 Nexter Munitions Dispositif d'amorcage a initiation electrique pour projectile

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE325292C (de) * 1918-06-11 1920-09-23 Siemens Schuckertwerke G M B H Doppelzuender fuer Granaten
US1531717A (en) * 1923-07-12 1925-03-31 Remondy Leon Emile Percussion fuse for aircraft bombs and other purposes
BE447865A (fr) * 1943-01-05
FR80976E (fr) * 1954-04-27 1963-07-12 Bombrini Parodi Delfino Spa Perfectionnements apportés aux amorces sensibles ou ultrasensibles à caractéristique d'autodestruction pyrique à retardement
BE565993A (fr) * 1954-04-27
DE1101225B (de) * 1960-05-19 1961-03-02 Rheinmetall Gmbh Selbstzerlegerzuender
CH368076A (fr) * 1961-02-24 1963-03-15 Mefina Sa Fusée pour projectile
CH425549A (de) * 1965-04-23 1966-11-30 Junghans Geb Ag Drallgeschosszünder für Übungsgeschosse
US3633510A (en) * 1970-08-05 1972-01-11 Us Navy Dual mode fuze explosive train
DE2242930C2 (de) * 1972-08-31 1987-01-02 Rheinmetall GmbH, 4000 Düsseldorf Hohlladungstochtergeschoß
CH606978A5 (en) * 1975-08-21 1978-11-30 Raymond Cerf Hand grenade combined impact and delay fuse

Also Published As

Publication number Publication date
US4736682A (en) 1988-04-12
DE3574494D1 (de) 1990-01-04
NO863090D0 (no) 1986-07-31
WO1986003828A1 (fr) 1986-07-03
DE3446314A1 (de) 1986-06-19
EP0236325A1 (fr) 1987-09-16
NO863090L (no) 1986-07-31

Similar Documents

Publication Publication Date Title
EP0763705B1 (fr) Projectile secondaire pour projectile du type tandem
EP0583642A1 (fr) Engin explosif emportant deux charges placées en tandem
DE19983923B4 (de) Selbstzerstörender Aufprallzünder
DE3416787A1 (de) Panzerbrechendes geschoss
EP0318995B1 (fr) Allumeur pyrotechnique pour projectiles
EP0236325B1 (fr) Detonateur auto-destructeur
DE4335022C2 (de) Zünd- und Sicherungseinrichtung mit Selbstzerlegungseinrichtung für ein mit einer Hohlladungseinlage versehenes Granatengeschoß
EP3014213B1 (fr) Détonateur pour grenade de mortier et grenade de mortier pouvant être tirée par un mortier à ergot équipée d'un tel détonateur
EP0318996B1 (fr) Allumeur pyrotechnique pour projectiles, roquettes bombes et mines
EP0233208B1 (fr) Fusee a double effet pour projectiles
DE3441556A1 (de) Aufschlagzuender
EP0387675A2 (fr) Fusée de fond pour grenade
EP1370825A1 (fr) Dispositif d'allumage dote d'un dispositif de securite, destine a un projectile devant etre tire d'un tube avec un moment angulaire
EP0227919B1 (fr) Fusée d'impact pour projectile
DE2310668A1 (de) Aufschlagzuender
EP0499701A1 (fr) Dispositif de sécurité pour projectile destiné à être lancé à partir d'un tube
EP0913663B1 (fr) Allumeur d'impact pyrotechnique
DE19726951C2 (de) Zünder für ein Drallgeschoß mit im Verriegelungsbolzen für den Detonatorträger angeordneter Selbstzerlegereinheit
DE3935316C2 (fr)
DE1147516B (de) Handgranatenzuender
WO1987001192A1 (fr) Fusee a double effet pour projectiles
DE3539279A1 (de) Zuender fuer ein fallschirm- oder bandstabilisiertes bomblet
DE1578193C (de) Leuchtgeschoss
DE1158876B (de) Mechanischer Aufschlagzuender fuer ein Raketengeschoss
EP0247451A2 (fr) Sécurité de bouche pour munition d'exercice

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19870320

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH DE FR GB IT LI LU NL SE

17Q First examination report despatched

Effective date: 19880916

ITF It: translation for a ep patent filed
GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE CH DE FR GB IT LI LU NL SE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Effective date: 19891129

REF Corresponds to:

Ref document number: 48310

Country of ref document: AT

Date of ref document: 19891215

Kind code of ref document: T

REF Corresponds to:

Ref document number: 3574494

Country of ref document: DE

Date of ref document: 19900104

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19901029

Year of fee payment: 6

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19901107

Ref country code: AT

Effective date: 19901107

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19901108

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19901130

Ref country code: LI

Effective date: 19901130

Ref country code: CH

Effective date: 19901130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Effective date: 19910601

GBPC Gb: european patent ceased through non-payment of renewal fee
NLV4 Nl: lapsed or anulled due to non-payment of the annual fee
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19920731

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

EUG Se: european patent has lapsed

Ref document number: 85905808.3

Effective date: 19910705

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19971115

Year of fee payment: 13

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19990901