EP0918210A2 - Safety device for a projectile fuze - Google Patents

Safety device for a projectile fuze Download PDF

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Publication number
EP0918210A2
EP0918210A2 EP98121468A EP98121468A EP0918210A2 EP 0918210 A2 EP0918210 A2 EP 0918210A2 EP 98121468 A EP98121468 A EP 98121468A EP 98121468 A EP98121468 A EP 98121468A EP 0918210 A2 EP0918210 A2 EP 0918210A2
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EP
European Patent Office
Prior art keywords
rotor
ignition
detonators
control
control rotor
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
EP98121468A
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German (de)
French (fr)
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EP0918210A3 (en
EP0918210B1 (en
Inventor
Wolfgang von Entress-Fürsteneck
Fritz Müller
Werner Rüdenauer
Manfred Klare
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Diehl Stiftung and Co KG
Original Assignee
Diehl Stiftung and Co KG
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Publication of EP0918210A2 publication Critical patent/EP0918210A2/en
Publication of EP0918210A3 publication Critical patent/EP0918210A3/en
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Publication of EP0918210B1 publication Critical patent/EP0918210B1/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
    • F42C15/188—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier

Definitions

  • the invention relates to a safety device for detonators of warheads according to the preamble of claim 1.
  • Such safety devices are intended to unlock the detonators depending perform certain criteria automatically or in the case of a Malfunction will cause the fuse to block in the fuse.
  • each detonator comprise at least two securing elements must, independently of each other, the inadvertent release of the fuse and thus prevent the main charge from igniting.
  • Each of these must Securing elements from at least one not also through to the other element acting environmental force.
  • the invention has for its object a safety device for detonators to create warheads that only exist in the correct two Sequence of occurring and independent physical criteria unlocked.
  • the security requirements are met by the measures according to the invention according to MIL-STD-1316 and according to STANAG 4187.
  • One occurs at the detonator direct locking of the control rotor via a mechanical connection between a magnet and the control rotor by an additional one Locking pin. Due to these measures, the control rotor is through the recoil mass secured, its release by the launch acceleration done, and secured by the locking pin to the magnet, whose Unlocking is done by the electrical signal of the missile launch.
  • a second ignition means for the control rotor or the fuse of the second Rotors are carried out by a backflow.
  • the securing device for an igniter of a warhead for missiles, Missiles or the like starts from two rotors, one of which is the first rotor a control rotor 1 and the second rotor is an ignition rotor 2, both by an external toothing are in gear connection with each other.
  • the drive of the Control rotor 1 takes place in principle by the launch acceleration of the missile.
  • the rotational movement and the direction of rotation of the control rotor 1 determined by a radially outward center of gravity.
  • the ignition rotor 2 has a radially outward center of gravity, which makes it easy to carry is facilitated by the control rotor 1 via the toothing 3.
  • a two-armed lever 5 acts on an electromagnetic locking device 4, which is pivotable about the axis 6. At the free end of the lever 5 is in the middle Area connected a locking pin 7 for a recoil mass.
  • a additional locking pin 8 is with the outer end of the second lever arm connected and engages in the control rotor 1.
  • This Design means a direct locking of the control rotor 1 by the additionally attached to the lever 5 locking pin with the electromagnetic Locking device 4. In this way, the control rotor 1 is once through Backfire mass secured. The control rotor 1 is unlocked by Accelerated launch of the warhead with the missile.
  • the second fuse forms the additional locking pin 8 in connection with the electromagnetic Locking device 4, the unlocking by the electrical signal of the rocket launch.
  • control rotor 1 and the ignition rotor 2 are in one section Warhead 9 shown.
  • the two rotors 1 and 2 are by external teeth 3 back in gearbox connection.
  • Located in the two rotors 1 and 2 transfer charges 10 and 11.
  • There are two around the control rotor 1 180 ° opposing detonators 12 and 13 are provided, which are in corresponding Channels or recesses 14 and 15 of the warhead 9 are located.
  • the channels 14 and 15 and with them the detonators 12 and 13 are thereby coaxial aligned with the axis of rotation of the control rotor 1.
  • Figure 3 is made up of the three superimposed representations of the Rotors together.
  • the top illustration in FIG. 3 shows the securing position, the middle representation reveals the transition position and the lower representation shows the unlocked ignition position.
  • both rotors are equipped with centers of gravity from the center are offset radially outwards from or from the axis of rotation. For example, this will reached through the recesses 16 and 17 in the rotors.
  • the detonators 12 and 13 can be seen, each in this example are assigned to one of the rotors. Detonators 12 and 13 are in Holes of a security base plate. Furthermore, in the control rotor 1 and Ignition rotor 2, the ignition transformer 11 and 10 shown.
  • a first locking pin 7 engages in the control rotor 1, while the second locking pin 8 in the Movement path of the ignition rotor 2 is used.
  • the locking pins 7 and 8 are firmly attached to a common device, for example lever 5. How 3 can be seen, the locking pin 7 with an escapement gear 18 in operative connection. Are in this securing position the transfer charges 10 and 11 of the two rotors 1 and 2 outside the positions of the detonators 12 and 13. Only by a rotary movement, caused by the acceleration of the warhead at the launch of the missile the transfer charges move according to the direction of rotation of the two rotors 1 and 2 to the positions of the detonators 12 and 13. The synchronous process is guaranteed by the double-sided toothing 3.
  • the locking pin 8 remains in position via the lever 5.
  • This desired mechanical locking of the ignition rotor 2 according to FIG. 3 is made possible by the fact that the recirculation mass was increased and a additional locking pin 8 has been used, which is directly mechanically in the Ignition rotor 2 engages. By this measure, the ignition rotor 2 is double mechanical locked by the recoil mass and by the interlocking with the Control rotor.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Lock And Its Accessories (AREA)
  • Air Bags (AREA)
  • Retarders (AREA)

Abstract

The rocket has control (1) and firing (2) rotors carrying a priming charges (10, 11). A base plate carries detonators (12, 13). A safety pin (7) locks the control rotor and a further pin (8) is in the path of the firing rotor, both mounted on a lever (5). The rocket acceleration when the propellant is ignited causes the rotors to rotate moving the priming charges towards the detonators. An electrical signal releases the safety pins when the rocket is fired.

Description

Die Erfindung betrifft eine Sicherungseinrichtung für Zünder von Gefechtsköpfen nach dem Oberbegriff von Patentanspruch 1.The invention relates to a safety device for detonators of warheads according to the preamble of claim 1.

Derartige Sicherungseinrichtungen sollen die Entsicherung von Zündern in Abhängigkeit von bestimmten Kriterien selbsttätig durchführen oder im Falle einer Fehlfunktion eine Blockierung des Zünders in der Sicherstellung bewirken.Such safety devices are intended to unlock the detonators depending perform certain criteria automatically or in the case of a Malfunction will cause the fuse to block in the fuse.

Aus der Militärnorm MIL-STD-1316 ist die Forderung bekannt, daß das Sicherungssystem eines jeden Zünders mindestens zwei Sicherungselemente umfassen muß, die unabhängig voneinander die unbeabsichtigte Entsicherung des Zünders und damit die Zündung der Hauptladung verhindern können. Dabei muß jedes dieser Sicherungselemente von mindestens einer nicht auch durch auf das andere Element einwirkenden umweltbedingten Kraft betätigt werden.From the military standard MIL-STD-1316 the requirement is known that the security system of each detonator comprise at least two securing elements must, independently of each other, the inadvertent release of the fuse and thus prevent the main charge from igniting. Each of these must Securing elements from at least one not also through to the other element acting environmental force.

Aus der US-PS 3,994,231 ist eine Sicherungseinrichtung für Raktengefechtsköpfe bekannt, die eine Zündkette mit mechanischen und elektrischen Entsicherungsschritten enthält. Hierbei wird einerseits der Druck eines gezündeten Raketentriebwerkes verwendet, um einen Kolben zu bewegen, und andererseits ein von einem Rotor betätigter Schalter, um einen Schritt im Ablauf der Entsicherung auszuführen. Es sind jedoch keine Mittel zur Verarbeitung zweier voneinander unabhängiger Kriterien angegeben.From US Pat. No. 3,994,231 is a security device for missile warheads known, the ignition chain with mechanical and electrical unlocking steps contains. Here, on the one hand, the pressure of an ignited rocket engine used to move a piston, and on the other hand one of a rotor operated switch to perform a step in the unlocking process. However, there are no means of processing two of them independently Criteria specified.

Der Erfindung liegt die Aufgabe zugrunde, eine Sicherungseinrichtung für Zünder von Gefechtsköpfen zu schaffen, die nur bei Vorhandensein von zwei in der richtigen Reihenfolge auftretenden und voneinander unabhängigen physikalischen Kriterien entsichert. The invention has for its object a safety device for detonators to create warheads that only exist in the correct two Sequence of occurring and independent physical criteria unlocked.

Diese Aufgabe wird erfindungsgemäß durch die Merkmale des Patentanspruches 1 gelöst. Vorteilhafte Weiterbildungen und Ausbildungen der Erfindung sind in den Unteransprüche beschrieben.This object is achieved by the features of claim 1 solved. Advantageous further developments and developments of the invention are in the Subclaims described.

Durch die erfindungsgemäßen Maßnahmen werden die Sicherheitsanforderungen nach MIL-STD-1316 und gemäß STANAG 4187 erfüllt. Bei dem Zünder tritt eine direkte Verriegelung des Steuerungsrotors über eine mechanische Verbindung zwischen einem Magneten und dem Steuerungsrotor durch einen zusätzlich angebrachten Sicherungsstift ein. Aufgrund dieser Maßnahmen ist der Steuerungsrotor durch die Rückschießmasse gesichert, dessen Entsicherung durch die Abschußbeschleunigung erfolgt, und durch den Sicherungsstift zum Magneten gesichert, dessen Entsicherung durch das elektrische Signal des Flugkörperstartes geschieht.The security requirements are met by the measures according to the invention according to MIL-STD-1316 and according to STANAG 4187. One occurs at the detonator direct locking of the control rotor via a mechanical connection between a magnet and the control rotor by an additional one Locking pin. Due to these measures, the control rotor is through the recoil mass secured, its release by the launch acceleration done, and secured by the locking pin to the magnet, whose Unlocking is done by the electrical signal of the missile launch.

Zusätzlich zu dieser vorgeschilderten Maßnahme kann entsprechend der Erfindung ein zweites Zündmittel für den Steuerungsrotor oder die Sicherung des zweiten Rotors durch eine Rückschleßmasse ausgeführt werden.In addition to this described measure, according to the invention a second ignition means for the control rotor or the fuse of the second Rotors are carried out by a backflow.

Weitere Einzelheiten der Erfindung sind der nachfolgenden Zeichnungsbeschreibung zu entnehmen. Darin zeigen

Figur 1
einen Schnitt durch den Steuerungsrotor
Figur 2
einen Schnitt durch die miteinander in Eingriff stehenden Steuerungsrotor und Sicherungsrotor
Figur 3
in schematischer Darstellung die Rückschießmasse mit zusätzlichem Sicherungsstift für den Sicherungsrotor.
Further details of the invention can be found in the following description of the drawings. Show in it
Figure 1
a section through the control rotor
Figure 2
a section through the interlocking control rotor and safety rotor
Figure 3
a schematic representation of the recoil mass with an additional locking pin for the locking rotor.

Die Sicherungseinrichtung für einen Zünder eines Gefechtskopfes für Flugkörper, Raketen oder dergleichen geht aus von zwei Rotoren, von denen der erste Rotor ein Steuerungsrotor 1 und der zweite Rotor ein Zündrotor 2 ist, die beide durch eine Außenverzahnung miteinander in Getriebeverbindung stehen. Der Antrieb des Steuerungsrotors 1 erfolgt im Prinzip durch die Abschußbeschleunigung des Flugkörpers. Dabei wird die Drehbewegung und die Drehrichtung des Steuerungsrotors 1 durch einen radial nach außen verlegten Schwerpunkt bestimmt. Der Zündrotor 2 besitzt einen radial nach außen gelegten Schwerpunkt, wodurch seine Mitnahme durch den Steuerungsrotor 1 über die Verzahnung 3 erleichtert wird.The securing device for an igniter of a warhead for missiles, Missiles or the like starts from two rotors, one of which is the first rotor a control rotor 1 and the second rotor is an ignition rotor 2, both by an external toothing are in gear connection with each other. The drive of the Control rotor 1 takes place in principle by the launch acceleration of the missile. The rotational movement and the direction of rotation of the control rotor 1 determined by a radially outward center of gravity. The ignition rotor 2 has a radially outward center of gravity, which makes it easy to carry is facilitated by the control rotor 1 via the toothing 3.

An eine elektromagnetische Schließeinrichtung 4 greift ein zweiarmiger Hebel 5 an, der um die Achse 6 schwenkbar ist. An dem freien Ende des Hebels 5 ist im mittleren Bereich ein Sicherungsstift 7 für eine Rückschießmasse angeschlossen. Ein zusätzlicher Sicherungsstift 8 ist mit dem äußeren Ende des zweiten Hebelarms verbunden und greift in der Sicherstellung in den Steuerungsrotor 1 ein. Diese Bauweise bedeutet eine direkte Verriegelung des Steuerungsrotors 1 durch den zusätzlich am Hebel 5 angebrachten Sicherungsstift mit der elektromagnetischen Schließeinrichtung 4. Auf diese Weise ist der Steuerungsrotor 1 einmal durch die Rückschießmasse gesichert. Die Entsicherung des Steuerungsrotors 1 erfolgt durch Abschußbeschleunigung des Gefechtskopfes mit dem Flugkörper. Die zweite Sicherung bildet der zusätzliche Sicherungsstift 8 in Verbindung mit der elektromagnetischen Schließeinrichtung 4, wobei die Entsicherung durch das elektrische Signal des Raketenstarts erfolgt.A two-armed lever 5 acts on an electromagnetic locking device 4, which is pivotable about the axis 6. At the free end of the lever 5 is in the middle Area connected a locking pin 7 for a recoil mass. A additional locking pin 8 is with the outer end of the second lever arm connected and engages in the control rotor 1. This Design means a direct locking of the control rotor 1 by the additionally attached to the lever 5 locking pin with the electromagnetic Locking device 4. In this way, the control rotor 1 is once through Backfire mass secured. The control rotor 1 is unlocked by Accelerated launch of the warhead with the missile. The second fuse forms the additional locking pin 8 in connection with the electromagnetic Locking device 4, the unlocking by the electrical signal of the rocket launch.

In Figur 2 sind der Steuerungsrotor 1 und der Zündrotor 2 im Schnitt in einem Gefechtskopf 9 dargestellt. Die beiden Rotoren 1 und 2 sind durch eine Außenverzahnung 3 wieder in Getriebeverbindung. In den beiden Rotoren 1 und 2 befinden sich Übertragungsladungen 10 und 11. An den Steuerungsrotor 1 sind zwei um 180° gegenüberliegende Detonatoren 12 und 13 vorgesehen, die sich in entsprechenden Kanälen oder Ausnehmungen 14 und 15 des Gefechtskopfes 9 befinden. Die Kanäle 14 und 15 und mit ihnen die Detonatoren 12 und 13 sind dadurch koaxial zur Drehachse des Steuerungsrotors 1 ausgerichtet.In Figure 2, the control rotor 1 and the ignition rotor 2 are in one section Warhead 9 shown. The two rotors 1 and 2 are by external teeth 3 back in gearbox connection. Located in the two rotors 1 and 2 transfer charges 10 and 11. There are two around the control rotor 1 180 ° opposing detonators 12 and 13 are provided, which are in corresponding Channels or recesses 14 and 15 of the warhead 9 are located. The channels 14 and 15 and with them the detonators 12 and 13 are thereby coaxial aligned with the axis of rotation of the control rotor 1.

Der Vorteil der vorbeschriebenen Sicherungsmaßnahme besteht darin, daß zum Zündrotor 2 und damit zum Zündübertrager 11 ein Detonator nicht mehr vorhanden ist. Damit kann dieser Zündübertrager 11, der ausschließlich Sekundärsprengstoff beinhaltet, nicht mehr initiiert werden. Eine mögliche fehlerhafte Scharfstellung des Zündrotors 2 ist demzufolge kein sicherungskritischer Fall mehr. Ohne weitere Maßnahmen wäre die Funktionszuverlässigkeit einer an sich gewünschten redundanten Zündkette reduziert. Deshalb werden zum Steuerungsrotor 1 die zwei um 180° zueinander versetzt eingebauten elektrischen Detonatoren 12 und 13 eingebaut, wodurch die völlige Funktionszuverlässigkeit der Zündereinrichtung hergestellt ist.The advantage of the security measure described above is that Ignition rotor 2 and thus a detonator to ignition transmitter 11 is no longer available is. So that this ignition transmitter 11, the only secondary explosive involves no longer being initiated. A possible incorrect focus of the ignition rotor 2 is therefore no longer a safety-critical case. Without further measures would be the functional reliability of a desired one redundant ignition chain reduced. Therefore, the two control rotor 1 electrical detonators 12 and 13 installed offset from one another by 180 °, which produces the complete reliability of the igniter device is.

Die Figur 3 setzt sich aus den drei übereinander gezeichneten Darstellungen der Rotoren zusammen. Die oberste Darstellung in Figur 3 zeigt die Sicherungsposition, die mittlere Darstellung offenbart die Übergangsposition und die untere Darstellung zeigt die entsicherte Zündposition. In allen drei Darstellungen bedeuten gleiche Bezugszeichen gleiche Bauteile.Figure 3 is made up of the three superimposed representations of the Rotors together. The top illustration in FIG. 3 shows the securing position, the middle representation reveals the transition position and the lower representation shows the unlocked ignition position. Mean in all three representations same reference numerals same components.

In der Sicherungsposition sind die beiden getrieblich durch eine Verzahnung miteinander verbundenen Rotoren, nämlich Steuerungsrotor 1 und Zündrotor 2 zu erkennen. Aus dieser schematisch stark vereinfachten Darstellung ist auch ersichtlich, daß beide Rotoren mit Schwerpunkten ausgestattet sind, die vom Mittelpunkt aus bzw. von der Drehachse aus radial nach außen versetzt sind. Dies wird beispielsweise durch die Ausnehmungen 16 und 17 in den Rotoren erreicht. In den Rotoren sind die Detonatoren 12 und 13 erkennbar, die in diesem Beispiel jeweils einem der Rotoren zugeordnet sind. Die Detonatoren 12 und 13 befinden sich in Bohrungen einer Sicherheitsgrundplatte. Ferner sind im Steuerungsrotor 1 und im Zündrotor 2 die Zündübertrager 11 und 10 dargestellt. Ein erster Sicherungsstift 7 greift in den Steuerungsrotor 1 ein, während der zweite Sicherungsstift 8 in die Bewegungsbahn des Zündrotors 2 eingesetzt ist. Die Sicherungsstifte 7 und 8 sind an einer gemeinsamen Vorrichtung, beispielsweise Hebel 5, fest angebracht. Wie aus der oberen Darstellung von Figuren 3 ersichtlich ist, steht der Sicherungsstift 7 mit einem Hemmgetriebe 18 in Wirkverbindung. In dieser Sicherungsposition befinden sich die Übertragungsladungen 10 und 11 der beiden Rotoren 1 und 2 außerhalb der Positionen der Detonatoren 12 und 13. Erst durch eine Drehbewegung, die durch die Beschleunigung des Gefechtskopfes beim Start des Flugkörpers hervorgerufen wird, wandern die Übertragungsladungen entsprechend der Drehrichtung der beiden Rotoren 1 und 2 zu den Positionen der Detonatoren 12 und 13. Der synchrone Ablauf wird durch die beiderseitige Verzahnung 3 gewährleistet. Der Sicherungsstift 8 verbleibt in Position über den Hebel 5. In the locking position, the two are geared together by a gear connected rotors, namely control rotor 1 and ignition rotor 2 detect. From this schematically highly simplified representation it can also be seen that both rotors are equipped with centers of gravity from the center are offset radially outwards from or from the axis of rotation. For example, this will reached through the recesses 16 and 17 in the rotors. In the Rotors, the detonators 12 and 13 can be seen, each in this example are assigned to one of the rotors. Detonators 12 and 13 are in Holes of a security base plate. Furthermore, in the control rotor 1 and Ignition rotor 2, the ignition transformer 11 and 10 shown. A first locking pin 7 engages in the control rotor 1, while the second locking pin 8 in the Movement path of the ignition rotor 2 is used. The locking pins 7 and 8 are firmly attached to a common device, for example lever 5. How 3 can be seen, the locking pin 7 with an escapement gear 18 in operative connection. Are in this securing position the transfer charges 10 and 11 of the two rotors 1 and 2 outside the positions of the detonators 12 and 13. Only by a rotary movement, caused by the acceleration of the warhead at the launch of the missile the transfer charges move according to the direction of rotation of the two rotors 1 and 2 to the positions of the detonators 12 and 13. The synchronous process is guaranteed by the double-sided toothing 3. The locking pin 8 remains in position via the lever 5.

Die untere Darstellung von Figur 3 zeigt nun die entsicherte Zündposition, in welcher die Übertragungsladungen 10 und 11 exakt in die Positionen der Detonatoren eingeschwenkt sind.The lower representation of Figure 3 now shows the unlocked ignition position, in which the transfer charges 10 and 11 exactly in the positions of the detonators are swung in.

Diese gewünschte mechanische Verriegelung des Zündrotors 2 gemäß der Figur 3 ist dadurch möglich geworden, daß die Rückschleßmasse vergrößert wurde und ein zusätzlicher Sicherungsstift 8 eingesetzt worden ist, der direkt mechanisch in den Zündrotor 2 eingreift. Durch diese Maßnahme ist der Zündrotor 2 doppelt mechanisch verriegelt durch die Rückschießmasse und durch die Verzahnung mit dem Steuerungsrotor.This desired mechanical locking of the ignition rotor 2 according to FIG. 3 is made possible by the fact that the recirculation mass was increased and a additional locking pin 8 has been used, which is directly mechanically in the Ignition rotor 2 engages. By this measure, the ignition rotor 2 is double mechanical locked by the recoil mass and by the interlocking with the Control rotor.

Claims (4)

Sicherungseinrichtung für Zünder von Gefechtsköpfen mit zwei durch eine Außenverzahnung miteinander verbundene Rotoren, von denen der erste Rotor ein Steuerungsrotor (1) und der zweite Rotor ein Zündrotor (2) ist, die beide radial nach außen verlegte Schwerpunkte besitzen und durch die Gefechtskopfbeschleunigung ihre Drehenergie erhalten,
dadurch gekennzeichnet,
daß der Steuerungsrotor (1) durch eine mechanische Verbindung zwischen einer elektromagnetischen Schließeinrichtung (4) und dem Steuerungsrotor (1) zusätzlich zur Rückschießmasse verriegelt ist.Securing device for detonators of warheads with two rotors connected to each other by external teeth, of which the first rotor is a control rotor (1) and the second rotor is an ignition rotor (2), both of which have centers of gravity which are shifted radially outwards and receive their rotational energy through the warhead acceleration ,
characterized,
that the control rotor (1) is locked by a mechanical connection between an electromagnetic locking device (4) and the control rotor (1) in addition to the recoil mass. Sicherungseinrichtung nach Anspruch 1,
dadurch gekennzeichnet,
daß die mechanische Verbindung durch einen Sicherungsstift (8) erfolgt, der an einem doppelarmigen Hebel (5) angebunden ist, dessen zweiter Arm mit der elektromagnetischen Schließeinrichtung (4) verbunden ist.Security device according to claim 1,
characterized,
that the mechanical connection is made by a locking pin (8) which is connected to a double-armed lever (5), the second arm of which is connected to the electromagnetic locking device (4). Sicherungseinrichtung nach einem der vorgenannten Ansprüche,
dadurch gekennzeichnet,
daß der Steuerungsrotor (1) durch zwei um 180° zueinander versetzt eingebaute Detonatoren (12,13) beaufschlagt ist, während dem Zündrotor (2) ein Detonator nicht zugeordnet ist.Security device according to one of the preceding claims,
characterized,
that the control rotor (1) is acted upon by two detonators (12, 13) installed offset from one another by 180 °, while a detonator is not assigned to the ignition rotor (2). Sicherungseinrichtung nach einem der vorgenannten Ansprüche,
dadurch gekennzeichnet,
daß der Zündrotor (2) mit dem Steuerungsrotor (1) zusätzlich zur Verzahnung (3) durch einen Sicherungsstift (8) verriegelt ist, welcher direkt in den Zündrotor (2) mechanisch eingreift.Security device according to one of the preceding claims,
characterized,
that the ignition rotor (2) is locked to the control rotor (1) in addition to the toothing (3) by a locking pin (8) which mechanically engages directly in the ignition rotor (2).
EP98121468A 1997-11-21 1998-11-11 Safety device for a projectile fuze Expired - Lifetime EP0918210B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19751499 1997-11-21
DE19751499A DE19751499A1 (en) 1997-11-22 1997-11-22 Security device for detonators of warheads

Publications (3)

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EP0918210A2 true EP0918210A2 (en) 1999-05-26
EP0918210A3 EP0918210A3 (en) 2000-09-27
EP0918210B1 EP0918210B1 (en) 2004-02-11

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EP98121468A Expired - Lifetime EP0918210B1 (en) 1997-11-21 1998-11-11 Safety device for a projectile fuze

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DE (2) DE19751499A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1624178A1 (en) * 2004-08-05 2006-02-08 Diehl BGT Defence GmbH & Co.KG Rocket motor
CN116147438A (en) * 2022-12-09 2023-05-23 北京理工大学 Reversible fuze safety system

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3994231A (en) 1971-12-08 1976-11-30 The United States Of America As Represented By The Secretary Of The Navy Guided missile warhead fuze

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3498225A (en) * 1958-10-07 1970-03-03 Us Navy Counter-rotating dual rotor safety and arming mechanism
US3906861A (en) * 1974-01-21 1975-09-23 Us Navy Fuze sterilization system
US4337701A (en) * 1980-01-28 1982-07-06 The United States Of America As Represented By The Secretary Of The Navy Electromechanical warhead safety-arming device

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3994231A (en) 1971-12-08 1976-11-30 The United States Of America As Represented By The Secretary Of The Navy Guided missile warhead fuze

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1624178A1 (en) * 2004-08-05 2006-02-08 Diehl BGT Defence GmbH & Co.KG Rocket motor
CN116147438A (en) * 2022-12-09 2023-05-23 北京理工大学 Reversible fuze safety system

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Publication number Publication date
DE59810745D1 (en) 2004-03-18
DE19751499A1 (en) 1999-05-27
EP0918210A3 (en) 2000-09-27
EP0918210B1 (en) 2004-02-11

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