EP0236325B1 - Self-destroying igniter - Google Patents

Self-destroying igniter Download PDF

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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
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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
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German (de)
French (fr)
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EP0236325A1 (en
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
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Rheinmetall GmbH
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Publication date
Application filed by Rheinmetall GmbH filed Critical Rheinmetall GmbH
Priority to AT85905808T priority Critical patent/ATE48310T1/en
Publication of EP0236325A1 publication Critical patent/EP0236325A1/en
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Publication of EP0236325B1 publication Critical patent/EP0236325B1/en
Expired legal-status Critical Current

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    • 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.

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Abstract

An explosive head comprises a casing to receive an explosive charge and an igniter casing, connected to the first casing, wherein there is arranged an impact igniter. The impact igniter comprises a needle (1) which co-operates with a detonator (8). In order to obtain a self-destroying effect, the needle (1) is hollow and comprises, arranged from back to front in a recess, an igniting primer composition (1a), a pyrotechnical retardation element (1b) and an outgoing igniter composition (1c). A needle (7) is fixed in the igniter casing (12) so as to co-operate with the priming igniter composition (1a). In the case of a failure of the detonator (8) impacted by the needle (1d) when hitting the target, the outgoing igniter composition (1c) is actuated via the pyrotechnical retardation element (1b), after the priming igniter composition (1a) has been primed by the needle (7), thereby detonating the failing detonator (8) and finally activating the explosive charge (10a) through the transmission charge (9).

Description

Die Erfindung betrifft einen Gefechtskopf nach dem Oberbegriff des Patentanspruches 1.The invention relates to a warhead according to the preamble of claim 1.

Ein derartiger Gefechtskopf ist aus der DE-A-2 242 930 bekannt. Der bekannte Gefechtskopf umfaßt ein Gefechtskopfgehäuse zur Aufnahme einer Hohlladung sowie einen mit dem Gefechtskopfgehäuse verbundenen, eine in Axialrichtung bewegbar gelagerte Zündnadel umfassenden Aufschlagzünder. Der Gefechtskopf wird in einer größeren Anzahl von einem Flugkörper oder Trägergeschoß über ein Zielgebiet transportiert und dort ausgestoßen. Beim Zielaufprall schnellt die Zündnadel infolge ihrer Massenträgheit vor und zündet einen querverschiebbaren Detonator, der seinerseits die Ladung des Gefechtskopfes, vorzugsweise eine Hohlladung, zur Detonation bringt.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. In the event of a target impact, 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.

Der Erfindung liegt die Aufgabe zugrunde, diesen bekannten Gefechtskopf um eine Selbstzerlegungsmöglichkeit zu erweitern.The invention is based, to expand this known warhead by a self-disassembly the task.

Ausgehend von dem Gefechtskopf der gattungsgemäßen Art wird diese Aufgabe durch die im Kennzeichnungsteil des Patentanspruches 1 angegebenen Merkmale gelöst.Starting from the warhead of the generic type, this object is achieved by the features specified in the characterizing part of patent claim 1.

Aus der DE-B-1 101 225 ist ein ogivenförmiger, spitzenseitig in einem großkalibrigen drallstabilisierten Artilleriegeschoß angeordneter Aufschlagzünder mit Selbstzerlegereinrichtung bekannt. Obgleich einige bauteilmäßige Übereinstimmungen der bekannten Zünderanordnung mit dem erfindungsgemäßen Gefechtskopf vorliegen, funktioniert die bekannte Zünderanordnung jedoch nach einem völlig anderen Wirkungsprinzip: Bei Abschuß aus der Rohrwaffe soll durch einen in der hohlen Zündnadel/Schlagstück gegen die Kraft einer Druckfeder verschiebbaren Anzündsatz eine Verzögerungsladung gezündet werden. Nach erfolgter Beschleunigung im Rohr wird der Anzündsatz jedoch durch die Druckfeder sofort wieder von der Verzögerungsladung getrennt; eine sichere Anzündung kann daher nicht gewährleistet werden. Nachteiligerweise ist ein Mittel zum Axialverschieben der hohlen Zündnadel nach Abbrand der Anzündladung und weiteren Verzögerungsladung nicht gegebdn. Ein Herausheben derZündnadel aus einer Sicherungsausnehmung aus dem Detonatorträger und dessen Querverschieben ist gleichfalls nicht sichergestellt. Die hohl ausgebildete Zündnadel enthält viele weitere Bauelemente, wodurch sie sehr lang ausgebildet und eine Verwendung im konstruktiv wesentlich kleineren Gefechtskopf (Bomblet) unmöglich ist. Die Zündnadel dieses bekannten Artilleriegeschosses wirkt nicht durch Massenträgheit entgegen der Flugrichtung; damit sie wirksam werden kann, muß das Geschoß spitzenseitig soweit verformt werden, daß der hohlzylindrische Schlagkörper mit der Zündnadel nach hinten in den Detonator eingeschlagen wird. Hierbei besteht jedoch die große Gefahr, daß bei Deformation der Geschoßspitze der lange rohrförmige Schlagkörper festgeklemmt wird und eine Zündung unterbleibt. Ebenso wird das Geschoß bei weichem Zielaufprall z.B. im Schnee oder weichem Boden oder bei ganz flachem Zielaufprall spitzenseitig nicht deformiert und gezündet. Aufgrund des nicht definierten Abstandes der Zündnadel bzw. des Schlagkörpers zum Detonatorträger bzw. der Detonatorladung ist eine sicher funktionierende Selbstzerlegung über den Verzögerungszündsatz bzw. dem Selbstzerlegezündsatz höchst zweifelhaft.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. Although there are some structural similarities of the known detonator arrangement with the warhead according to the invention, 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. Disadvantageously, there is no means for axially displacing the hollow firing needle after the ignition charge has burned off and further retarding charge. Likewise, lifting the ignition needle out of a securing recess from the detonator carrier and displacing it transversely is not ensured. 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. Here, however, there is a great risk that the long tubular impact body is clamped when the projectile tip is deformed and ignition does not occur. In the case of a soft target impact, 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.

Bei dem erfindungsgemäßen Bomblet ist das Zündergehäuse demgegenüber heckseitig angeordnet, beide Zündnadeln weisen in Flugrichtung, die zweite Zündnadel für den Verzögerungszündsatz ist ortsfest angeordnet, während die erste Zündnadel durch ihre Massenträgheitskraft bei Zielaufprall störungsfrei in die Detonatorladung getrieben wird. Bei weichem Zielaufprall ist aufgrund der geringen Bauhöhe und der kurzen Abstände zwischen Ausgangszündsatz und Detonatorladung eine sichere Durchzündung und Selbstzerlegung gewährleistet.In the case of the bomblet according to the invention, on the other hand, 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. In the event of a soft 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.

Vorteilhafte Ausgestaltungen der Erfindung gehen aus den Unteransprüchen hervor.Advantageous embodiments of the invention emerge from the subclaims.

Die Erfindung bietet den Vorteil, daß die eigene Truppe gegebenenfalls gefährdende Blindgänger weitgehend vermieden werden, da die Selbstzerlegereinrichtung auch im Falle des Versagens des Aufschlagzünders die Gefechtsladung des Gefechtskopfes aktiviert und damit unschädlich macht. Darüberhinaus ist damit jedoch eine Steigerung der Zuverlässigkeit des Gefechtskopfes verbunden, da selbst bei Versagen des Aufschlagzünders die Selbstzerlegereinrichtung die Gefechtsladung noch zur Detonation bringen kann und damit den Gefechtskopf zielwirksam werden läßt.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.

Die Erfindung wird nachfolgend unter Bezug auf die Zeichnung näher erläutert. Dabei zeigt:

  • Fig. 1 in schematischer Darstellung als Seitenansicht einen Gefechtskopf der gattungsgemäßen Art;
  • Fig. 2 eine vergrößerte Schnittdarstellung des Zünderteils des Gefechtskopfes.
The invention is explained in more detail below with reference to the drawing. It shows:
  • Figure 1 is a schematic side view of a warhead of the generic type.
  • Fig. 2 is an enlarged sectional view of the igniter part of the warhead.

Fig. 1 zeigt in schematischer Darstellung einen Gefechtskopf 10 in Seitenansicht. Der Gefechtskopf 10 umfaßt ein Gefechtskopfgehäuse 11 zur Aufnahme einer Gefechtsladung, vorzugsweise einer Hohlladung. Mit dem Gefechtskopfgehäuse 11 ist ein heckseitig angeordnetes Zündergehäuse 12 verbunden, das einen Aufschlagzünder enthält. Am Zündergehäuse ist eine Drallbremse 13 befestigt, die nach Ausstoßen des Gefechtskopfes 10 aus dem drallstabilisierten Trägergeschoß die Drallzahl reduziert und die Flugstabilität des Gefechtskopfes 10 beim Hinabsinken auf das Zielgebiet verbessert.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. With the warhead housing 11, 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.

Der Aufschlagzünder (Fig. 2) umfaßt eine Zündnadel 1, die in gesicherter Stellung festgelegt, im entsicherten Zustand aber axial beweglich angeordnet ist und dabei mit einem Detonator 8 zusammenwirkt, der gegebenenfalls vermittels einer Übertragungsladung 9 die Gefechtsladung 10 zur Detonation bringt.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.

Erfindungsgemäß ist die Zündnadel 1 hohl ausgebildet und trägt in ihrer Ausnehmung in folgender Reihe, heckseitig beginnend, einen Anstichzündsatz 1 a, eine pyrotechnische Verzögerungsstrecke 1 b, sowie einen Ausgangszündsatz 1 c. Ortsfest im Zündergehäuse 12 ist weiter eine Nadel 7 angeordnet, die mit dem Anstichzündsatz 1 a zusammenwirkt.According to the invention, 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.

Die Wirkungsweise der Selbstzerleger- und Zündeinrichtung ist wie folgt: Ausgegangen wird von der in Fig. 2 dargestellten Sicherstellung, in der die Zündnadel 1 durch in Radialrichtung entfernbare schieberartig ausgebildete Sicherungsmittel 5 festgelegt ist und demzufolge auch bei Stoßbeanspruchung sich nicht in Axialrichtung fortbewegen kann. Die Spitze 1 b der Zündnadel 1 liegt dabei in einer Blindbohrung des von einer Druckfeder 8d beaufschlagten und in Radialrichtung ausfahrbar angeordneten Detonatorträgers 8c und verhindert dadurch dessen Ausweichen in Radialrichtung. Nach dem Entsichern, d.h. Entfernen der Sicherungsmittel 5 in Radialrichtung drückt die in Axialrichtung wirkende Druckfeder 6 die Zündnadel 1 in Heckrichtung zurück, wobei die gehäusefest angeordnete Nadel 7 den Anstichzündsatz 1 a aktiviert, der wiederum die pyrotechnische Verzögerungsstrecke 1 b in Funktion setzt. Gleichzeitig ist die Spitze 1 d aus der Blindbohrung 8b hinausgeglitten und hat den Detonatorträger 8c freigegeben, der nunmehr federbelastet in Radialrichtung derart ausschwenkt, daß der Detonator 8 unter der Spitze 1 d der Zündnadel 1 zu liegen kommt und dabei mit der Übertragungsladung 9 fluchtet und somit eine pyrotechnische Anzündkette zur Gefechtsladung 10 herstellt. Die Spitze 1 d der Zündnadel 1 befindet sich bis zum Zielaufprall des Gefechtskopfes in Zündbereitschaftsstellung oberhalb des Detonators 8. Beim Zündaufprall schnellt die Zündnadel 1 infolge ihrer Massenträgheit gegen die Kraft der Druckfeder 6 in Axialrichtung vor und sticht dabei den Detonator 8 an, der seinerseits vermittels der Übertragungsladung 9 die Gefechtsladung 10 zur Detonation bringt. Im Falle eines Zündversagers dieser Anzündkette wirkt ergänzend die Selbstzerlegereinrichtung. Mittlerweile ist nämlich die pyrotechnische Verzögerungsstrecke 1 bis zum Ausgangszündsatz 1 durchgebrannt und aktiviert diesen, wodurch eine Flammfront durch die Bohrungen 1e im Bereich der Nadel 1 hindurchtritt und den fehlerhafterweise nicht aktivierten Detonator 8 mit einer derart hohen Temperatur beaufschlagt, daß er trotzdem noch in Funktion tritt. Dadurch ist sichergestellt, daß auch bei Versagen der Hauptanzündkette zumindest eine Selbstzerlegung des Gefechtskopfes eintritt Regelmäßig wird jedoch die Selbstzerlegereinrichtung noch dafür sorgen, daß selbst bei Versagen der Hauptzündkette die Gefechtsladung 1 Oa noch rechtzeitig detoniert und damit der Gefechtskopf 10 bestimmungsgemäß zielwirksam wird.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. After unlocking, ie removing the securing means 5 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. At the same time, 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. In the event of a firing impact, 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. In the event of an ignition failure of this ignition chain, the self-disassembly device also acts. In the meantime, 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 . This ensures that even if the main firing chain fails, the warhead will self-disassemble at regular intervals. However, 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.

In einem weiteren Ausführungsbeispiel der Erfindung wird der Ausgangszündsatz 1 c vorteilhaft detonativ ausgebildet, wodurch sich eine noch größere Sicherheit zur Aktivierung der Gefechtsladung 10a erreichen läßt.In a further exemplary embodiment of the invention, 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.

In einem Ausführungsbeispiel der Erfindung wurde die Brenndauer der pyrotechnischen Verzögerungsstrecke 1 b auf etwa 8-10 Sekunden bemessen. Die pyrotechnische Verzögerungsstrecke bestand dazu aus einer an sich bekannten pyrotechnischen Zusammensetzung mit einem Durchmesser von etwa 3 mm und einer Umhüllung mit einer Dicke von etwa 1,5 mm; die gesamte Länge der pyrotechnischen Verzögerungsstrecke betrug etwa 18 mm.In one embodiment of the invention, the burning time of the pyrotechnic delay line 1 b was dimensioned to be about 8-10 seconds. For this purpose, 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.

Claims (3)

1. Warhead, a large number of which are to be accommodated in a missile or carrier projectile from which the warhead is ejected over a target area, the warhead having a warhead housing (11) designed to accommodate a warhead charge (10a), particularly a hollow charge, and a detonator housing (12) which is situated on the rear part of the warhead (10) and contains an impact fuse and which in turn comprises a first detonating needle (1) displaceable in the longitudinal axial direction and interacting with a transversally displaceable detonator (8), characterised by the following features:
the detonating needle (1) is of hollow construction, the recess containing, in the following order and starting with the rear, a broaching fuse composition (1 a), a pyrotechnic delay section (1 b) and an output fuse composition (1c),
in the detonator housing (12) a second detonating needle (7) interacting with the broaching fuse composition (1 a) is provided in a fixed position on the inside of the end wall forming the rear termination,
the first detonating needle (1), ), after ejection from the carrier projectile and after release by securing means (5), can be moved towards the rear by the resilient force of a pressure spring (6) situated coaxially around the first detonating needle (1) in the detonator housing (12), the broaching fuse composition (1 a) being thereby rendered active, the first detonating needle (1) and the second detonating needle (7) point in the direction of flight of the warhead (10), and
the first detonating needle (1) is so constructed that on impact with the target and as a result of the mass inertia is displaceable in the axial direction towards the detonator (8), in opposition to the force of the pressure spring (6).
2. Warhead in accordance with Claim 1, characterised by the fact that apertures (1 e) forthe passage of the flame are provided in the zone of the point (1 d) of the detonating needle (1).
3. Warhead in accordance with anyone of Claims 1 and 2 characterised by the fact that the output fuse composition (1c) is constructed to act as a detonator.
EP85905808A 1984-12-19 1985-11-07 Self-destroying igniter Expired EP0236325B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT85905808T ATE48310T1 (en) 1984-12-19 1985-11-07 SELF DECOMPOSITION IGNITION.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843446314 DE3446314A1 (en) 1984-12-19 1984-12-19 SKULL HEAD
DE3446314 1984-12-19

Publications (2)

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EP0236325A1 EP0236325A1 (en) 1987-09-16
EP0236325B1 true EP0236325B1 (en) 1989-11-29

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EP85905808A Expired EP0236325B1 (en) 1984-12-19 1985-11-07 Self-destroying igniter

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US (1) US4736682A (en)
EP (1) EP0236325B1 (en)
DE (2) DE3446314A1 (en)
NO (1) NO863090L (en)
WO (1) WO1986003828A1 (en)

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* 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 (en) * 1992-03-23 1998-05-01 Garcia Garcia Jose TOTAL ACTION HAND GRENADE.
DE4335022C2 (en) * 1993-10-14 1998-06-10 Rheinmetall Ind Ag Ignition and safety device with self-dismantling device for a grenade projectile with a shaped charge insert
FR2959303B1 (en) * 2010-04-27 2012-04-06 Nexter Munitions ELECTRICALLY INITIATED STARTING DEVICE FOR PROJECTILE

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE325292C (en) * 1918-06-11 1920-09-23 Siemens Schuckertwerke G M B H Double fuse for grenades
US1531717A (en) * 1923-07-12 1925-03-31 Remondy Leon Emile Percussion fuse for aircraft bombs and other purposes
BE447865A (en) * 1943-01-05
FR80976E (en) * 1954-04-27 1963-07-12 Bombrini Parodi Delfino Spa Improvements to sensitive or ultra-sensitive primers with delayed pyric self-destruction characteristics
BE565993A (en) * 1954-04-27
DE1101225B (en) * 1960-05-19 1961-03-02 Rheinmetall Gmbh Self-destructing igniter
CH368076A (en) * 1961-02-24 1963-03-15 Mefina Sa Rocket for projectile
CH425549A (en) * 1965-04-23 1966-11-30 Junghans Geb Ag Twist projectile fuze for training projectiles
US3633510A (en) * 1970-08-05 1972-01-11 Us Navy Dual mode fuze explosive train
DE2242930C2 (en) * 1972-08-31 1987-01-02 Rheinmetall GmbH, 4000 Düsseldorf Hollow charge daughter floor
CH606978A5 (en) * 1975-08-21 1978-11-30 Raymond Cerf Hand grenade combined impact and delay fuse

Also Published As

Publication number Publication date
NO863090D0 (en) 1986-07-31
WO1986003828A1 (en) 1986-07-03
US4736682A (en) 1988-04-12
NO863090L (en) 1986-07-31
DE3446314A1 (en) 1986-06-19
DE3574494D1 (en) 1990-01-04
EP0236325A1 (en) 1987-09-16

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