EP0525305B1 - Launching device for tank self protection - Google Patents

Launching device for tank self protection Download PDF

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Publication number
EP0525305B1
EP0525305B1 EP92106652A EP92106652A EP0525305B1 EP 0525305 B1 EP0525305 B1 EP 0525305B1 EP 92106652 A EP92106652 A EP 92106652A EP 92106652 A EP92106652 A EP 92106652A EP 0525305 B1 EP0525305 B1 EP 0525305B1
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EP
European Patent Office
Prior art keywords
charge
missile
igniting
lead
launcher according
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
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EP92106652A
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German (de)
French (fr)
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EP0525305A1 (en
Inventor
Wolfgang Dipl.-Ing. Badura
Fritz Greindl
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.)
Buck Chemisch Technische Werke GmbH and Co
Buck Werke GmbH and Co
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Buck Chemisch Technische Werke GmbH and Co
Buck Werke GmbH and Co
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Publication of EP0525305A1 publication Critical patent/EP0525305A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C7/00—Fuzes actuated by application of a predetermined mechanical force, e.g. tension, torsion, pressure
    • F42C7/12—Percussion fuzes of the double-action type, i.e. fuzes cocked and fired in a single movement, e.g. by pulling an incorporated percussion pin or hammer
    • 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
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/68—Line-carrying missiles, e.g. for life-saving
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/145—Cartridges, i.e. cases with charge and missile for dispensing gases, vapours, powders, particles or chemically-reactive substances
    • F42B5/15—Cartridges, i.e. cases with charge and missile for dispensing gases, vapours, powders, particles or chemically-reactive substances for creating a screening or decoy effect, e.g. using radar chaff or infrared material
    • F42B5/155—Smoke-pot projectors, e.g. arranged on vehicles

Definitions

  • the invention relates to self-protection launchers, such as those used for protecting tanks.
  • the launcher device consists of a plurality of launcher tubes, which are attached to a suitable location on the outer surface of the tank, and throwing bodies inserted into the launcher tubes, which contain a propellant charge and an active charge, the latter mostly being a fog charge.
  • the firing of the throwing bodies takes place electrically from the inside of the tank, ignition contacts being arranged in the launch tube, which are in contact with contact rings located on the throwing body jacket.
  • Contactless namely inductive ignition systems are also known.
  • the electrical energy received via contacts or contactlessly is used to ignite the propellant charge, in which case the hot propellant gases in turn ignite the active charge via a pyrotechnic ignition chain with a delay element.
  • the safety and effectiveness of the protective measure are of particular importance in such a throwing device. So it must be ensured that there is no ignition of the active charge in the launch tube (pipe safety) or in the vicinity of the pipe mouth (front pipe safety and rail safety), the latter even then not if the missile hits an obstacle (tree) before it reaches its specified firing range. These safety problems also arise when the active charge is ignited not by a pyrotechnic ignition chain but by an impact detonator.
  • the effectiveness of the protective measure depends, on the one hand, on the accuracy of the missile and, on the other hand, on the time between the time the missile was fired and the onset of protection, i.e. the formation of the cloud of fog.
  • the throwing body In today's throwing devices of this type, the throwing body is usually shot at an angle of 45 ° with respect to the horizontal, so that the trajectory of the throwing body is very steep, which leads to a comparatively long flight time with the result that it takes effect late and also causes problems. to allow the active charge to take effect exactly at the desired height above the ground, because the throwing body gains high speed in the steep fall phase of its trajectory, with which even the smallest deviations in the ignition timing have a considerable influence. Due to the further development of the attack measures, one is now also forced to improve the protective measures, in particular to ensure that protective effects occur faster than before. For this reason, efforts are being made to change from the previous steep trajectories to much flatter trajectories, down to 10 °.
  • the object of the present invention is therefore to improve self-protection launcher devices of the type described so that safety and accuracy (to be defined later) are ensured even with a flat and short trajectory.
  • the solution to this problem results from the characterizing features of patent claim 1.
  • the projectile thus remains connected to the launch site after it has been fired via a safety line and this safety line is dimensioned in such a length that it reaches its full extent when the specified range is reached by the projectile, with the result that it has the
  • the throwing body brakes abruptly, tensioning the firing pin spring and releasing the firing pin so that it ignites the active charge, for example via a primer and an ignition charge.
  • the actual range of the missile is determined by the length of the safety line, which can be done very precisely and leads to an unusually high accuracy.
  • the firing pin spring is only tensioned by pulling the safety line and the firing pin is then released, which leads to very high tube, down tube and rail safety.
  • suspension line is slightly shorter than the range specified by the propellant charge or the propellant charge would allow the throwing body a slightly larger range than is permitted by the suspension line, because only then does the jerk required for tensioning the firing pin spring occur. If the throwing body hit the ground exactly at the distance from the launching point, which corresponds to the length of the line, there would be no ignition of the active charge. Even immediately before the desired meeting point, there is still a high level of security (final phase security).
  • the throwing body has a cup-like housing sleeve 10, the area adjacent to the cup base is thickened and the front cup opening of which is closed by a cover 11, which is also the base of a spontaneous active charge to be explained later; the lid 11 is held by means of a flanging of the sleeve edge, a sealing ring 12 ensuring a watertight closure.
  • the secondary side of an inductive ignition system consisting of a ferrite core 13 and a transformer coil 14, is attached to the bottom of the cup.
  • a comparatively massive and heavy anchor cover 15 with a central bore sits on the bottom of the cup, on which in turn a propellant chamber housing 16 is seated, which contains a propellant charge 17 filled with propellant charge 17 18 surrounds.
  • the propellant charge chamber 18 is covered by a thin film against the central bore of the anchor cover 15, in which an ignition pill 19 is located.
  • a suspension line primary part 21 which consists of comparatively short suspension lines which are held at one end on the drive chamber housing 16 and at the other ends on the anchor cover 15, which in turn is attached to the cup base by means of a separating element 22 and a time delay piece 23.
  • Six primary lines 21 of this type are provided coaxially to the longitudinal axis of the throwing body.
  • a drum 24 is seated for the secondary secondary line 25, which consists of a comparatively long secondary line, with its one end is attached to the drum 24 and with its other end to a central piece 26 which is held in the central opening of the ring base 27 of a point mist body container to be explained later.
  • a central support tube 28 From the central opening of the ring base 27 there is a central support tube 28, in which a piston rod 29 is slidably mounted, which is attached at one end to the central piece 26 and at the other end is connected to a firing pin 31 by means of a coupling piece 30.
  • a firing pin spring is designated.
  • a point mist charge 33 consisting of ring bodies is accommodated, which is covered on the end side by a compensating disk 42 and on the other hand by an ignition distributor cover 34.
  • the ignition distributor cover 34 contains an ignition cap 35, which is located in the path of movement of the firing pin 31, a transmission charge 36, a delay piece 37 and an ignition charge 38 for the point mist charge 33.
  • a spontaneous mist body 39 is arranged on the outside of the ignition distributor cover 34, in which is in extension to the firing pin axis an ignition-splitter charge 40 which is connected to the transfer charge 36 via an opening in the ignition distributor cover 34.
  • the point mist body container 41 is connected to the spontaneous mist body 39 via coupling pins 43, so that an active charge double body results.
  • the anchor cover 15 with the separating element 22 and the delay piece 23 and the secondary part 13, 14 of the ignition system remain in the launch tube.
  • the primary part 21 of the suspension line which is fastened at one end to the propellant charge housing 16, is carried along with the throwing body double body.
  • the length of the six individual lines of the primary part 21 is such that they are completely tensioned when the double body has left the mouth of the housing sleeve 10, at which point in time the propellant charge 17 also burned off.
  • An example value for the length of the primary part 21 of the safety line is 0.5 m.
  • the projectile is, for example, at a distance of 45 m from the launch site and at a height of 4.5 m above the ground.
  • the ignition occurs in such a way that the secondary part 25 of the suspension line pulls jerkily on the central piece 26, with the result that the firing pin 31 is pulled backwards via the piston rod 29, the spring 22 being tensioned.
  • the "jerk” mentioned is damped in such a way that comparatively small suspension line cross sections can be used; the damping results on the one hand from the elasticity of the tether system and on the other hand through the air column 44, which is compressed by the piston rod 29.
  • the firing pin 31 strikes against a stop, and as a result of the further pulling of the suspension line on The central piece 26 and thus on the piston rod 29 tears the coupling piece 30, that is, the connection between the piston rod 29 and firing pin 31 is released, so that the firing pin 31 strikes forward against the primer 35 by the now relaxing spring 32.
  • This movement is supported by the inertia of the firing pin.
  • the primer 35 struck by the firing pin 31 ignites the transfer charge 36, which in turn ignites the igniter charge 40, which leads to a spontaneous development of fog due to the fog charge 39; the transfer charge 36 also ignites the time delay piece 37, which, after a certain time delay, ignites the ignition charges 38, with the result that the point fog charge 33 begins to form fog.
  • the hot propellant gases generated when the propellant charge 17 burned off also ignited the time delay element 23 via a suitable channel. Its time delay is such that when the point mist body has reached the bottom, for example 2 seconds after firing, it has burned out and ignites the separating device 22, which releases the connection on the anchor cover 15 to the housing sleeve 10; The lines are therefore separated from the part of the throwing body remaining in the launch tube. This is also indicated in sketch D of FIG. 2.
  • the safety line system ensures an exact ignition at the desired distance from the firing point, at a predetermined height above the ground.
  • the throwing body like the Exemplary embodiment, a double body
  • the problem is to put the double body into operation at a speed of about 150 km / h at a target point, the front body above the ground and the rear body on the ground to release a cloud of fog.
  • clouds of fog should mix, that is, they form an overall cloud standing spatially one above the other.
  • an extremely precise ignition is obviously required, and this is achieved with the safety line system described.
  • the interception of the propellant charge housing 16 and the drum 24 by the primary safety lines 21 shortly after the double body emerges from the mouth of the housing sleeve 10 is important; this means that the center of gravity is shifted forward on the double body, with the result of an exact flight of the double body with exact unwinding of the secondary suspension line.
  • the safety line system By dividing the safety line system into a primary part consisting of several safety lines and a secondary part consisting of only one safety line, a high safety line safety in the area of the hot propellant gases is achieved without taking up too much space and weight for the safety line system in the throwing body.
  • the front end of the secondary secondary line can also be divided into several individual secondary lines in order to obtain the most axial pull possible on the central piece 26.
  • a strain relief in the form of a clamping ring 45 is provided for the firing pin 31, which prevents tensioning of the firing pin spring 32 during the flight. Only the interception energy at the target point overcomes the clamping force of the ring 45 and then allows the spring 32 to be tensioned.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)

Description

Die Erfindung betrifft Selbstschutz-Werfereinrichtungen, wie sie beispielsweise zum Schutz von Panzern eingesetzt werden. Dabei besteht die Werfereinrichtung aus einer Mehrzahl von Werferrohren, die an einer geeigneten Stelle der Außenfläche des Panzers befestigt sind, und aus in die Werferrohre eingesetzten Wurfkörpern, die eine Treibladung und eine Wirkladung beinhalten, wobei es sich bei letzterer meist um eine Nebelladung handelt. Die Zündung der Wurfkörper erfolgt elektrisch vom Panzerinneren aus, wobei im Abschußrohr Zündkontakte angeordnet sind, die mit am Wurfkörpermantel befindlichen Kontaktringen in Berührung stehen. Bekannt sind aber auch kontaktlose, nämlich induktive Zündsysteme. Im Wurfkörper wird die über Kontakte oder kontaktlos empfangene elektrische Energie zur Zündung der Treibladung genutzt, wobei dann die heißen Treibgase ihrerseits über eine pyrotechnische Zündkette mit Verzögerungsstück die Wirkladung anzünden.The invention relates to self-protection launchers, such as those used for protecting tanks. The launcher device consists of a plurality of launcher tubes, which are attached to a suitable location on the outer surface of the tank, and throwing bodies inserted into the launcher tubes, which contain a propellant charge and an active charge, the latter mostly being a fog charge. The firing of the throwing bodies takes place electrically from the inside of the tank, ignition contacts being arranged in the launch tube, which are in contact with contact rings located on the throwing body jacket. Contactless, namely inductive ignition systems are also known. In the projectile, the electrical energy received via contacts or contactlessly is used to ignite the propellant charge, in which case the hot propellant gases in turn ignite the active charge via a pyrotechnic ignition chain with a delay element.

Von besonderer Bedeutung sind bei einer solchen Werfereinrichtung die Sicherheit und die Effektivität der Schutzmaßnahme. So muß gewährleistet sein, daß es nicht zu einer Zündung der Wirkladung im Abschußrohr (Rohrsicherheit) oder in der Nähe der Rohrmündung (Vorrohrsicherheit und Bahnsicherheit) kommt, letzteres auch dann nicht, wenn der Wurfkörper vor Erreichen seiner vorgegebenen Schußweite auf ein Hindernis (Baum) trifft. Diese Sicherheitsprobleme ergeben sich im übrigen auch dann, wenn die Wirkladung nicht durch eine pyrotechnische Zündkette sondern durch einen Aufschlagzünder gezündet wird. Die Effektivität der Schutzmaßnahme hängt zum einen von der Treffgenauigkeit des Wurfkörpers und zum anderen von der Zeitspanne zwischen Zeitpunkt des Wurfkörper-Abschusses und Eintreten des Schutzes, also etwa Bildung der Nebelwolke, ab.The safety and effectiveness of the protective measure are of particular importance in such a throwing device. So it must be ensured that there is no ignition of the active charge in the launch tube (pipe safety) or in the vicinity of the pipe mouth (front pipe safety and rail safety), the latter even then not if the missile hits an obstacle (tree) before it reaches its specified firing range. These safety problems also arise when the active charge is ignited not by a pyrotechnic ignition chain but by an impact detonator. The effectiveness of the protective measure depends, on the one hand, on the accuracy of the missile and, on the other hand, on the time between the time the missile was fired and the onset of protection, i.e. the formation of the cloud of fog.

Bei den heutigen derartigen Werfereinrichtungen wird der Wurfkörper meist unter einem Winkel von 45° gegenüber der Horizontalen abgeschossen, so daß die Flugbahn des Wurfkörpers sehr steil ist, was zu einer vergleichsweise langen Flugzeit mit der Folge eines späten Wirksamwerdens führt und darüberhinaus Probleme mit sich bringt, die Wirkladung exakt in der gewünschten Höhe über Boden wirksam werden zu lassen, weil der Wurfkörper in der steilen Sturzphase seiner Flugbahn eine hohe Geschwindigkeit erhält, womit schon kleinste Abweichungen des Zündzeitpunkts beträchtlichen Einfluß erlangen. Durch die Weiterentwicklung der Angriffsmaßnahmen ist man aber nun auch gezwungen, die Schutzmaßnahmen zu verbessern, insbesondere dafür zu sorgen, daß Schutzwirkungen schneller als bisher eintreten. Aus diesem Grund ist man bestrebt, von den bisherigen steilen Flugbahnen auf wesentlich flachere Flugbahnen überzugehen, und zwar bis zu 10° herunter. Damit wird nicht nur die Flugdauer beträchtlich vermindert, sondern auch die Einhaltung der gewünschten Wirkungshöhe über Boden erleichtert. Andererseits wird es schwieriger, die Treffgenauigkeit in horizontaler Erstreckung einzuhalten und vor allem bereitet es Probleme, die Sicherheit, insbesondere die Vorrohr- und Bahnsicherheit, zu gewährleisten. Dabei ist zu berücksichtigen, daß beispielsweise bei einer Panzer-Selbstschutzeinrichtung die Schußweite der Wurfkörper bei 40 bis 50 Meter liegen soll, welche Entfernung bei flacher Flugbahn vom Wurfkörper in kürzester Zeit durchflogen wird. Untersuchungen haben ergeben, daß mit den heutigen pyrotechnischen Zündketten es kaum möglich ist, die erforderliche Sicherheit und die gewünschte Treffgenauigkeit einwandfrei zu gewährleisten.In today's throwing devices of this type, the throwing body is usually shot at an angle of 45 ° with respect to the horizontal, so that the trajectory of the throwing body is very steep, which leads to a comparatively long flight time with the result that it takes effect late and also causes problems. to allow the active charge to take effect exactly at the desired height above the ground, because the throwing body gains high speed in the steep fall phase of its trajectory, with which even the smallest deviations in the ignition timing have a considerable influence. Due to the further development of the attack measures, one is now also forced to improve the protective measures, in particular to ensure that protective effects occur faster than before. For this reason, efforts are being made to change from the previous steep trajectories to much flatter trajectories, down to 10 °. This not only considerably reduces the flight duration, but also makes it easier to maintain the desired effective height above the ground. On the other hand, it becomes more difficult to maintain the accuracy in the horizontal extension and, above all, it creates problems to ensure the safety, in particular the safety of the pipe and rail. It should be taken into account that, for example, in the case of a tank self-protection device, the range of the missile should be 40 to 50 meters, which distance in a short time is flown by the missile with a flat trajectory. Studies have shown that with today's pyrotechnic ignition chains it is hardly possible to guarantee the required security and the desired accuracy.

Aufgabe der vorliegenden Erfindung ist es deshalb, Selbstschutz-Werfereinrichtungen der beschriebenen Art so zu verbessern, daß auch bei flacher und kurzer Flugbahn Sicherheit und Treffgenauigkeit (wird später noch definiert) gewährleistet sind. Die Lösung dieser Aufgabe ergibt sich aus den kennzeichnenden Merkmalen des Patentanspruchs 1.The object of the present invention is therefore to improve self-protection launcher devices of the type described so that safety and accuracy (to be defined later) are ensured even with a flat and short trajectory. The solution to this problem results from the characterizing features of patent claim 1.

Gemäß der Erfindung bleibt also das Wurfgeschoß nach seinem Abschuß über eine Fangleine mit dem Abschußort in Verbindung und diese Fangleine ist in ihrer Länge so bemessen, daß sie bei Erreichen der vorgegebenen Schußweite durch den Wurfkörper ihre volle Erstreckung erhält, mit der Folge, daß sie den Wurfkörper ruckartig abbremst und dabei die Schlagbolzenfeder spannt und den Schlagbolzen freigibt, so daß dieser, etwa über ein Zündhütchen und einen Anzündsatz, die Wirkladung entzündet. Die tatsächliche Schußweite des Wurfkörpers wird also durch die Länge der Fangleine festgelegt, was sehr exakt erfolgen kann und zu einer ungewöhnlich hohen Treffgenauigkeit führt. Darüberhinaus wird die Schlagbolzenfeder erst durch den Zug der Fangleine gespannt und der Schlagbolzen dann freigegeben, was zu einer sehr hohen Rohr-, Vorrohr- und Bahnsicherheit führt. Dabei ist wesentlich, daß die Fangleine geringfügig kürzer ist als der durch die Treibladung vorgegebenen Schußweite entspricht bzw. die Treibladung dem Wurfkörper eine etwas größere Schußweite ermöglichen würde als von der Fangleine zugelassen wird, weil nur dann der für das Spannen der Schlagbolzenfeder erforderliche Ruck auftritt. Würde der Wurfkörper exakt in der Entfernung vom Abschußpunkt auf den Erdboden auftreffen, die der Leinenlänge entspricht, würde es nicht zu einer Entzündung der Wirkladung kommen. Selbst unmittelbar vor der gewünschten Treffstelle besteht also noch eine hohe Sicherheit (Endphasensicherheit).According to the invention, the projectile thus remains connected to the launch site after it has been fired via a safety line and this safety line is dimensioned in such a length that it reaches its full extent when the specified range is reached by the projectile, with the result that it has the The throwing body brakes abruptly, tensioning the firing pin spring and releasing the firing pin so that it ignites the active charge, for example via a primer and an ignition charge. The actual range of the missile is determined by the length of the safety line, which can be done very precisely and leads to an unusually high accuracy. In addition, the firing pin spring is only tensioned by pulling the safety line and the firing pin is then released, which leads to very high tube, down tube and rail safety. It is essential that the suspension line is slightly shorter than the range specified by the propellant charge or the propellant charge would allow the throwing body a slightly larger range than is permitted by the suspension line, because only then does the jerk required for tensioning the firing pin spring occur. If the throwing body hit the ground exactly at the distance from the launching point, which corresponds to the length of the line, there would be no ignition of the active charge. Even immediately before the desired meeting point, there is still a high level of security (final phase security).

Besonders zweckmäßige Ausgestaltungen der Erfindung sind in den Unteransprüchen gekennzeichnet.Particularly expedient embodiments of the invention are in the Subclaims marked.

Auf der Zeichnung ist eine Ausführungsform der Erfindung beispielsweise dargestellt. Es zeigen:

Fig. 1
einen Wurfkörper der Werfereinrichtung im Längsschnitt und
Fig. 2
Skizzen zur Erläuterung der Funktionsweise der Werfereinrichtung bzw. des von diesen verschossenen Wurfkörpers.
In the drawing, an embodiment of the invention is shown for example. Show it:
Fig. 1
a throwing body of the launcher in longitudinal section and
Fig. 2
Sketches to explain the functioning of the launcher or the missile fired by it.

Der Wurfkörper weist eine becherartige Gehäusehülse 10 auf, deren dem Becherboden benachbarter Bereich verdickt ist und deren vordere Becheröffnung durch einen Deckel 11, der zugleich Boden einer später zu erläuternden Spontan-Wirkladung ist, verschlossen ist; der Deckel 11 wird mittels einer Umbördelung des Hülsenrandes gehalten, wobei ein Dichtring 12 für einen wasserdichten Verschluß sorgt. Am Becherboden ist die Sekundärseite eines induktiven Zündsystems befestigt, bestehend aus einem Ferritkern 13 und einer Transformatorspule 14. Auf dem Becherboden sitzt ein vergleichsweise massiver und schwerer Ankerdeckel 15 mit Mittelbohrung auf, auf dem wiederum ein Treibkammergehäuse 16 sitzt, das eine mit Treibladung 17 gefüllte Treibladungskammer 18 umgibt. Die Treibladungskammer 18 ist gegen die Mittelbohrung des Ankerdeckels 15, in welchem sich eine Zündpille 19 befindet, durch eine dünne Folie abgedeckt. In der durch das Treibkammergehäuse 16 abgedeckten Ausnehmung 20 am und im Ankerdeckel 15 befindet sich ein Fangleinen-Primärteil 21, das aus vergleichsweise kurzen Fangleinen besteht, die mit ihren einen Enden am Treibkammergehäuse 16 und mit ihren anderen Enden am Ankerdeckel 15 gehaltert sind, der seinerseits mittels eines Trennelements 22 und eines Zeitverzögerungsstück 23 am Becherboden befestigt ist. Koaxial zur Längsachse des Wurfkörpers sind sechs derartige Primär-Fangleinen 21 vorgesehen. Auf dem Treibkammergehäuse 16 sitzt eine Trommel 24 für das Fangleinen-Sekundärteil 25, welches aus einer vergleichsweise langen Fangleine besteht, die mit ihrem einen Ende an der Trommel 24 und mit ihrem anderen Ende an einem Zentralstück 26 befestigt ist, das in der Mittelöffnung des Ringbodens 27 eines später noch zu erläuternden Punktnebelkörper-Behälters gehaltert ist. Von der Mittelöffnung des Ringbodens 27 geht ein zentrales Stützrohr 28 ab, in welchem eine Kolbenstange 29 gleitbar gelagert ist, die mit ihrem einen Ende am Zentralstück 26 befestigt und mit ihrem anderen Ende mittels eines Kopplungsstücks 30 mit einem Schlagbolzen 31 verbunden ist. Mit 32 ist eine Schlagbolzenfeder bezeichnet. Im Ringraum zwischen erwähntem Punktnebelkörper-Behälter 41 und Stützrohr 28 ist eine aus Ringkörpern bestehende Punkt-Nebelladung 33 untergebracht, die stirnseitig einerseits von einer Ausgleichsscheibe 42 und andererseits von einem Anzündverteilerdeckel 34 abgedeckt ist. Der Anzündverteilerdeckel 34 enthält ein Anzündhütchen 35, das sich im Bewegungsweg des Schlagbolzens 31 befindet, eine Übertragungsladung 36, ein Verzögerungsstück 37 und einen Anzündsatz 38 für die Punkt-Nebelladung 33. Auf der Außenseite des Zündverteilerdeckels 34 ist ein Spontan-Nebelkörper 39 angeordnet, in welchem sich in Verlängerung zur Schlagbolzenachse eine Anzünd-Zerlegerladung 40 befindet, die über eine Öffnung im Anzündverteilerdeckel 34 mit der Übertragungsladung 36 in Verbindung steht. Der Punktnebelkörper-Behälter 41 ist mit dem Spontan-Nebelkörper 39 über Kupplungsstifte 43 verbunden, so daß sich ein Wirkladungs-Doppelkörper ergibt.The throwing body has a cup-like housing sleeve 10, the area adjacent to the cup base is thickened and the front cup opening of which is closed by a cover 11, which is also the base of a spontaneous active charge to be explained later; the lid 11 is held by means of a flanging of the sleeve edge, a sealing ring 12 ensuring a watertight closure. The secondary side of an inductive ignition system, consisting of a ferrite core 13 and a transformer coil 14, is attached to the bottom of the cup. A comparatively massive and heavy anchor cover 15 with a central bore sits on the bottom of the cup, on which in turn a propellant chamber housing 16 is seated, which contains a propellant charge 17 filled with propellant charge 17 18 surrounds. The propellant charge chamber 18 is covered by a thin film against the central bore of the anchor cover 15, in which an ignition pill 19 is located. In the recess 20 covered by the drive chamber housing 16 on and in the anchor cover 15 there is a suspension line primary part 21 which consists of comparatively short suspension lines which are held at one end on the drive chamber housing 16 and at the other ends on the anchor cover 15, which in turn is attached to the cup base by means of a separating element 22 and a time delay piece 23. Six primary lines 21 of this type are provided coaxially to the longitudinal axis of the throwing body. On the drive chamber housing 16, a drum 24 is seated for the secondary secondary line 25, which consists of a comparatively long secondary line, with its one end is attached to the drum 24 and with its other end to a central piece 26 which is held in the central opening of the ring base 27 of a point mist body container to be explained later. From the central opening of the ring base 27 there is a central support tube 28, in which a piston rod 29 is slidably mounted, which is attached at one end to the central piece 26 and at the other end is connected to a firing pin 31 by means of a coupling piece 30. With 32 a firing pin spring is designated. In the annular space between the aforementioned point mist body container 41 and the support tube 28, a point mist charge 33 consisting of ring bodies is accommodated, which is covered on the end side by a compensating disk 42 and on the other hand by an ignition distributor cover 34. The ignition distributor cover 34 contains an ignition cap 35, which is located in the path of movement of the firing pin 31, a transmission charge 36, a delay piece 37 and an ignition charge 38 for the point mist charge 33. A spontaneous mist body 39 is arranged on the outside of the ignition distributor cover 34, in which is in extension to the firing pin axis an ignition-splitter charge 40 which is connected to the transfer charge 36 via an opening in the ignition distributor cover 34. The point mist body container 41 is connected to the spontaneous mist body 39 via coupling pins 43, so that an active charge double body results.

Nachfolgend soll nun die Funktionsweise dieses Wurfkörpers erläutert werden. Für den Abschuß wird auf die im Boden des nicht-gezeichneten Abschußrohrs befindliche Primärseite des induktiven Zündsystems ein Stromstoß gegeben, mit der Folge, daß in der Sekundärspule 14 des Zündsystems ein Strom erzeugt wird, der über einen Leiterdraht die Zündpille 19 zündet. Diese wiederum zündet unter Durchschlagen der Abdeckfolie die Treibladung 17. Die sich nunmehr entwickelnden Treibgase gelangen über Bohrungen in einen Ringraum 15a, mit der Folge, daß der Doppelkörper 39, 41 des Wurfkörpers unter Öffnen des stirnseitigen Bördelrandes aus der Hülse 10 und somit aus dem nicht-gezeichneten Abschußrohr geschoben, also abgeschossen wird. Im Abschußrohr verbleiben neben der Hülse 10 der Ankerdeckel 15 mit Trennelement 22 und Verzögerungsstück 23 sowie der Sekundärteil 13, 14 des Zündsystems. Der mit seinem einen Ende am Treibladungsgehäuse 16 befestigte Primärteil 21 der Fangleine wird mit dem Wurfkörper-Doppelkörper mitgenommen. Dabei sind die sechs Einzelleinen des Primärteils 21 in ihrer Länge so bemessen, daß sie völlig gespannt sind, wenn der Doppelkörper die Mündung der Gehäusehülse 10 verlassen hat, zu welchem Zeitpunkt auch die Treibladung 17 abgebrannt ist. Ein Beispielswert für die Länge des Primärteils 21 der Fangleine ist 0,5 m. Sobald nun dieser Zeitpunkt der völligen Straffung des Primärteils 21 erreicht ist, halten die am Treibladungsgehäuse 16 befestigten Fangleinen das Treibladungsgehäuse 16 fest, so daß dieses ein kurzes Stück vor der Mündung der Gehäusehülse 10 "stehen bleibt", wohingegen der übrige Teil des Doppelkörpers weiterfliegt. Damit tritt nun der Sekundärteil 25 der Fangleine in Aktion, die ja zwischen stehenbleibendem Gehäuse 16 und weiterfliegendem Zentralstück 26 auf der Trommel 24 aufgewickelt ist und sich nunmehr abspult. Dieser Zeitpunkt entspricht der Skizze A von Fig. 2. Sobald nun der Fangleinen-Sekundärteil völlig abgespult und gespannt ist, zündet die Fangleine den Wurfkörper, welcher Zeitpunkt in Skizze B von Fig. 2 dargestellt ist; der Wurfkörper befindet sich dabei beispielsweise in einer Entfernung von 45 m vom Abschußort und in einer Höhe von 4,5 m über Boden. Die Zündung geschieht dabei in der Weise, daß der Sekundärteil 25 der Fangleine ruckartig am Zentralstück 26 zieht, mit der Folge, daß der Schlagbolzen 31 über die Kolbenstange 29 nach hinten gezogen wird, wobei sich die Feder 22 spannt. Zu erwähnen ist an dieser Stelle, daß der erwähnte "Ruck" derart gedämpft ist, daß mit vergleichsweise geringen Fangleinenquerschnitten auszukommen ist; die Dämpfung ergibt sich dabei einerseits durch die Dehnungsfähigkeit des Fangleinensystems und andererseits durch die Luftsäule 44, welche durch die Kolbenstange 29 komprimiert wird. Nach vollständiger Spannung der Feder 32 schlägt der Schlagbolzen 31 an einem Anschlag an, und infolge des weiteren Zugs der Fangleine am Zentralstück 26 und damit an der Kolbenstange 29 reißt das Kupplungsstück 30, daß heißt, die Verbindung zwischen Kolbenstange 29 und Schlagbolzen 31 wird gelöst, so daß der Schlagbolzen 31 durch die sich nun entspannende Feder 32 nach vorne gegen das Zündhütchen 35 schlägt. Dabei wird diese Bewegung noch durch die Trägheit des Schlagbolzens unterstützt. Das vom Schlagbolzen 31 getroffene Zündhütchen 35 entzündet die Übertragungsladung 36, die ihrerseits die Anzünd-Zerlegerladung 40 zündet, womit es durch die Nebelladung 39 zu einer spontanen Nebelentwicklung kommt; die Übertragungsladung 36 zündet aber zugleich auch das Zeitverzögerungsstück 37 an, das, nach einer gewissen Zeitverzögerung, die Anzündsätze 38 entzündet, mit der Folge, daß der Punkt-Nebelsatz 33 mit der Nebelbildung beginnt. Dieser Zeitpunkt, bei dem also der Spontan-Nebel noch besteht und der Punkt-Nebel gerade beginnt, ist in Skizze C von Fig. 2 dargestellt, wobei der Spontan-Nebel mit "A", der Punkt-Nebel mit "B" bezeichnet ist. Zu diesem Zeitpunkt hat der nebelnde, nun hintere Einzel-Nebelkörper den Boden erreicht. Mit fortschreitendem Zeitablauf erzeugt nur noch diese Punkt-Nebelladung 33 einen Nebel, was in Skizze D von Fig. 2 dargestellt ist.The mode of operation of this projectile will now be explained below. For the launch, a current surge is given to the primary side of the inductive ignition system located in the bottom of the launch tube, not shown, with the result that a current is generated in the secondary coil 14 of the ignition system, which ignites the squib 19 via a conductor wire. This in turn ignites the propellant charge 17 by penetrating the cover film. The propellant gases now developing pass through holes into an annular space 15a, with the result that the double body 39, 41 of the throwing body opens the sleeve 10 and thus does not open the front flanged edge -drawn Launch tube pushed, that is, shot down. In addition to the sleeve 10, the anchor cover 15 with the separating element 22 and the delay piece 23 and the secondary part 13, 14 of the ignition system remain in the launch tube. The primary part 21 of the suspension line, which is fastened at one end to the propellant charge housing 16, is carried along with the throwing body double body. The length of the six individual lines of the primary part 21 is such that they are completely tensioned when the double body has left the mouth of the housing sleeve 10, at which point in time the propellant charge 17 also burned off. An example value for the length of the primary part 21 of the safety line is 0.5 m. As soon as this point in time of the complete tightening of the primary part 21 is reached, the lines attached to the propellant charge housing 16 hold the propellant charge housing 16 firmly, so that it "stops" a short distance from the mouth of the casing sleeve 10, whereas the remaining part of the double body continues to fly. The secondary part 25 of the safety line now comes into action, which is wound on the drum 24 between the stationary housing 16 and the central part 26 which is still flying and now unwinds. This point in time corresponds to sketch A in FIG. 2. As soon as the secondary cord part has been completely unwound and tensioned, the catching line ignites the throwing body, which point in time is shown in sketch B in FIG. 2; the projectile is, for example, at a distance of 45 m from the launch site and at a height of 4.5 m above the ground. The ignition occurs in such a way that the secondary part 25 of the suspension line pulls jerkily on the central piece 26, with the result that the firing pin 31 is pulled backwards via the piston rod 29, the spring 22 being tensioned. It should be mentioned at this point that the "jerk" mentioned is damped in such a way that comparatively small suspension line cross sections can be used; the damping results on the one hand from the elasticity of the tether system and on the other hand through the air column 44, which is compressed by the piston rod 29. After the spring 32 is fully tensioned, the firing pin 31 strikes against a stop, and as a result of the further pulling of the suspension line on The central piece 26 and thus on the piston rod 29 tears the coupling piece 30, that is, the connection between the piston rod 29 and firing pin 31 is released, so that the firing pin 31 strikes forward against the primer 35 by the now relaxing spring 32. This movement is supported by the inertia of the firing pin. The primer 35 struck by the firing pin 31 ignites the transfer charge 36, which in turn ignites the igniter charge 40, which leads to a spontaneous development of fog due to the fog charge 39; the transfer charge 36 also ignites the time delay piece 37, which, after a certain time delay, ignites the ignition charges 38, with the result that the point fog charge 33 begins to form fog. This point in time at which the spontaneous fog still exists and the point fog is just beginning is shown in sketch C of FIG. 2, the spontaneous fog being labeled "A" and the point fog being labeled "B" . At this point, the foggy, now rear single smoke body has reached the ground. As time progresses, only this point fog charge 33 generates a fog, which is shown in sketch D of FIG. 2.

Es ist bisher nicht erwähnt worden, daß die beim Abbrennen der Treibladung 17 entstehenden heißen Treibgase über einen geeigneten Kanal auch das Zeitverzögerungsstück 23 angezündet haben. Dessen Zeitverzögerung ist so bemessen, daß es dann, wenn der Punktnebelkörper den Boden erreicht hat, beispielsweise 2 Sekunden nach Abschuß, durchgebrannt ist und die Trennvorrichtung 22 anzündet, welche die Verbindung am Ankerdeckel 15 zur Gehäusehülse 10 löst; die Fangleinen werden also vom im Abschußrohr verbliebenen Wurfkörperteil getrennt. Auch dies ist in Skizze D von Fig. 2 angedeutet.It has not previously been mentioned that the hot propellant gases generated when the propellant charge 17 burned off also ignited the time delay element 23 via a suitable channel. Its time delay is such that when the point mist body has reached the bottom, for example 2 seconds after firing, it has burned out and ignites the separating device 22, which releases the connection on the anchor cover 15 to the housing sleeve 10; The lines are therefore separated from the part of the throwing body remaining in the launch tube. This is also indicated in sketch D of FIG. 2.

Durch das Fangleinensystem wird trotz vorgegebener flacher Flugbahn des Wurfkörpers eine exakte Zündung in der gewünschten Entfernung vom Abschußort gewährleistet, und zwar in vorgegebener Höhe über Boden. Handelt es sich beim Wurfkörper, wie beim Ausführungsbeispiel, um einen Doppelkörper, dann besteht die Problematik darin, den Doppelkörper mit einer Geschwindigkeit von etwa 150 km/h in einem Zielpunkt in Funktion zu setzen, wobei der Frontkörper über dem Erdboden und der Heck-Körper am Boden eine Nebelwolke freisetzen soll. Beide Nebelwolken sollen sich vermischen, d.h., räumlich übereinander stehend eine Gesamtwolke bilden. Um dies zu erreichen ist offensichtlich eine äußerst exakte Zündung erforderlich, und diese wird mit dem beschriebenen Fangleinensystem erreicht. In diesem Zusammenhang ist auch das Abfangen des Treibladungsgehäuses 16 und der Trommel 24 durch die Primär-Fangleinen 21 kurz nach Austritt des Doppelkörpers aus der Mündung der Gehäusehülse 10 von Bedeutung; damit wird nämlich eine Schwerpunktsverlagerung am Doppelkörper nach vorne erreicht, mit der Folge eines exakten Flugs des Doppelkörpers mit exakter Abspulung der Sekundär-Fangleine.In spite of the flat trajectory of the projectile being flattened, the safety line system ensures an exact ignition at the desired distance from the firing point, at a predetermined height above the ground. Is it the throwing body, like the Exemplary embodiment, a double body, then the problem is to put the double body into operation at a speed of about 150 km / h at a target point, the front body above the ground and the rear body on the ground to release a cloud of fog. Both clouds of fog should mix, that is, they form an overall cloud standing spatially one above the other. To achieve this, an extremely precise ignition is obviously required, and this is achieved with the safety line system described. In this context, the interception of the propellant charge housing 16 and the drum 24 by the primary safety lines 21 shortly after the double body emerges from the mouth of the housing sleeve 10 is important; this means that the center of gravity is shifted forward on the double body, with the result of an exact flight of the double body with exact unwinding of the secondary suspension line.

Durch die Teilung des Fangleinensystems in einen aus mehreren Fangleinen bestehenden Primärteil und einen aus nur einer einzigen Fangleine bestehenden Sekundärteil wird eine hohe Fangleinensicherheit im Bereich der heißen Treibgase erreicht, ohne im Wurfkörper zuviel Platz und Gewicht für das Fangleinensystem zu beanspruchen. Selbstverständlich kann auch das Vorderende des Fangleinen-Sekundärteils in mehrere Einzelfangleinen aufgeteilt sein, um so einen möglichst axialen Zug am Zentralstück 26 zu erhalten.By dividing the safety line system into a primary part consisting of several safety lines and a secondary part consisting of only one safety line, a high safety line safety in the area of the hot propellant gases is achieved without taking up too much space and weight for the safety line system in the throwing body. Of course, the front end of the secondary secondary line can also be divided into several individual secondary lines in order to obtain the most axial pull possible on the central piece 26.

Zur Erhöhung der Sicherheit ist für den Schlagbolzen 31 eine Zugentlastung in Form eines Klemmrings 45 vorgesehen, der ein Spannen der Schlagbolzenfeder 32 während des Fluges verhindert. Erst die Abfangenergie am Zielpunkt überwindet die Klemmkraft des Rings 45 und läßt dann das Spannen der Feder 32 zu.To increase safety, a strain relief in the form of a clamping ring 45 is provided for the firing pin 31, which prevents tensioning of the firing pin spring 32 during the flight. Only the interception energy at the target point overcomes the clamping force of the ring 45 and then allows the spring 32 to be tensioned.

Die erwähnte Unterteilung der Wirkladung in einen Spontansatz und einen Punktsatz gewährleistet eine nahezu schlagartige Vernebelungswirkung, bei ausreichender Nebeldauer, erfordert aber die Zündexaktheit des beschriebenen Fangleinensystems.The above-mentioned subdivision of the active charge into a spontaneous charge and a point charge ensures an almost sudden nebulizing effect, with sufficient fog duration, but requires the ignition accuracy of the described safety line system.

Es ist besonders zweckmäßig, die Abschußrohre der Werfereinrichtung als Abschußmagazine gemäß der Patentanmeldung vom gleichen Tage mit der Veröffentlichungsnummer EP-A-0525304 auszubilden.It is particularly expedient to design the launching device's launching tubes as launching magazines according to the patent application dated the same day with the publication number EP-A-0525304.

Claims (9)

  1. A self-protection missile launcher which comprises a launch tube disposed on the item to be protected and has electrical igniting means on the tube base, a missile being disposed in the launch tube, the missile having a propulsion charge, an operative charge and means for igniting both charges, characterised in that the means for igniting the operative charge comprises a striking pin (31) and associated spring (32) and is connected to one end of a lead (21, 25), the same having its other end connected to the launch tube or to a part (15) remaining therein, the lead serving to cock the sprang (32) and actuate the striking pin (31), the lead (21, 25) being slightly shorter than the missile range determined by the propulsion charge (17).
  2. A launcher according to claim 1, characterised in that the lead comprises a primary part (21) and a secondary part (25), the primary part (21) having one end connected to a fixing cover (15) and the other end to a casing (16) for the propulsion charge, the cover (15) being disposed on the base of the missile casing (10) and remaining together therewith in the launch tube when the missile is launched, whereas the secondary part (25) of the lead has one end secured to the propulsion charge casing (16) and the other end to a piston rod (29) connected to the striking pin (31), and the propulsion charge casing (16) is a component releasable from the fixing cover (15) and from the operative section (29, 31, 32, 33, 29) of the missile.
  3. A launcher according to claim 2, characterised in that the primary part (21) of the lead comprises a number of individual leads disposed concentrically of the missile longitudinal axis.
  4. A launcher according to claim 2 or 3, characterised in that the piston rod (29) is connected to the striking pin (31) by way of a coupling element (30) having a frangible zone.
  5. A launcher according to any one of claims 1 to 4, characterised in that the missile contains a spontaneous smoke charge (39) ignitable by way of an igniting destructor charge (40) and a spot smoke charge ignitable by way of a delay element (37) and an igniting charge (38).
  6. A launcher according to claim 5, characterised in that both the igniting destructor charge (40) and the delay element (37) are ignitable by an igniting charge (36) which is ignitable by a priming cap (36) actuatable by the striking pin (31).
  7. A launcher according to any one of claims 2 to 6, characterised in that a pyrotechnical isolating element (22) is disposed at the fixing place of the fixing cover (15) and is preceded by a delay element (23) ignitable by the propelling gases of the propulsion charge (17).
  8. A launcher according to any one of claims 2 to 7, characterised in that the secondary part (13, 14) of an inductive igniting system is disposed on the base of the missile.
  9. A launcher according to any one of claims 1 to 9, characterised by an air spring (44) to damp the lead.
EP92106652A 1991-07-31 1992-04-16 Launching device for tank self protection Expired - Lifetime EP0525305B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4125355 1991-07-31
DE4125355A DE4125355C1 (en) 1991-07-31 1991-07-31

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EP0525305A1 EP0525305A1 (en) 1993-02-03
EP0525305B1 true EP0525305B1 (en) 1995-01-11

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EP (1) EP0525305B1 (en)
CA (1) CA2068399A1 (en)
DE (2) DE4125355C1 (en)

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FR2741435B1 (en) * 1995-11-17 1998-01-02 Giat Ind Sa PROJECTILE ALLOWING THE DISPERSION OF A PRODUCT ON A PATH
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US5272981A (en) 1993-12-28
DE59201177D1 (en) 1995-02-23
CA2068399A1 (en) 1993-02-01
EP0525305A1 (en) 1993-02-03
DE4125355C1 (en) 1993-01-28

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