EP0525305A1 - Launching device for tank self protection - Google Patents

Launching device for tank self protection Download PDF

Info

Publication number
EP0525305A1
EP0525305A1 EP92106652A EP92106652A EP0525305A1 EP 0525305 A1 EP0525305 A1 EP 0525305A1 EP 92106652 A EP92106652 A EP 92106652A EP 92106652 A EP92106652 A EP 92106652A EP 0525305 A1 EP0525305 A1 EP 0525305A1
Authority
EP
European Patent Office
Prior art keywords
charge
self
ignition
firing pin
protection
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
EP92106652A
Other languages
German (de)
French (fr)
Other versions
EP0525305B1 (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
Original Assignee
Buck Chemisch Technische Werke GmbH and Co
Buck Werke GmbH and Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Buck Chemisch Technische Werke GmbH and Co, Buck Werke GmbH and Co filed Critical Buck Chemisch Technische Werke GmbH and Co
Publication of EP0525305A1 publication Critical patent/EP0525305A1/en
Application granted granted Critical
Publication of EP0525305B1 publication Critical patent/EP0525305B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • 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 projectiles are ignited 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 casing of the projectile.
  • 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. 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 not even if the projectile hits an obstacle (tree) before it reaches its specified firing range meets. 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 launcher 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 consequence of being effective late and also causing 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 move 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 therefore 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 a primer.
  • the actual range of the throwing body is thus determined by the length of the suspension 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 launch 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 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 flange 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 sits, which contains a propellant charge chamber 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 bottom 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 for the secondary secondary line 25 which consists of a comparatively long safety line, which is attached at one end to the drum 24 and at the other end to a central piece 26 which is 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 transfer 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 located 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 double throwing 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 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, the coupling piece 30 breaks, that is to say the connection between the piston rod 29 and the firing pin 31 is released, so that the firing pin 31 strikes forward through the now relaxing spring 32 against the primer 35.
  • 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 piece 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 thus 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 launch site, at a predetermined height above the ground.
  • the throwing body as in the exemplary embodiment, is a double body
  • the problem is how to operate the double body at a speed of about 150 km / h at a target point, the front body above the ground and the rear body should release a cloud of fog on the ground. Both clouds of fog should mix, i.e., 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.
  • 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 possible pull 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.

Landscapes

  • 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)

Abstract

A self-defence launch device is improved, which consists of a firing tube, which is fitted on the object to be defended, has an electrical detonating device on the tube base and has an ejection body, which is inserted into the firing tube, with a propulsion charge and an ejection charge, as well as a detonating device for igniting the propulsion charge and effective charge. The effective charge detonating device is in this case a mechanical detonating device with an impact bolt and an impact bolt spring. This mechanical detonating device is cocked and released by means of a lanyard which is connected on the one hand to the firing tube or a part of the ejection body which remains in the firing tube, and on the other hand to the impact bolt. When, once it has been fired, the ejection body has reached a firing distance which corresponds to the length of the lanyard, the impact bolt spring is now cocked, by the lanyard which is now tensioned, and the impact bolt is thus released and then ignites the effective charge of the ejection body, via a detonating cap and a pyrotechnic detonating chain. <IMAGE>

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 projectiles are ignited 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 casing of the projectile. Contactless, namely inductive ignition systems are also known. In the throwing body, 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. 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 not even if the projectile hits an obstacle (tree) before it reaches its specified firing range meets. 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 launcher 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 consequence of being effective late and also causing 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 move from the previous steep trajectories to much flatter trajectories, down to 10. This not only significantly 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 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 safety and the desired accuracy.

Aufgabe der vorliegenden Erfindung ist es deshalb, Selbstschutz-Werfereinrichtungender 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 therefore 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 a primer. The actual range of the throwing body is thus determined by the length of the suspension 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 launch 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 configurations of the Invention are characterized in the subclaims.

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 shows a missile of the launcher in longitudinal section and
  • Fig. 2 sketches to explain the operation of the launcher or the missile fired by this.

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 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 flange 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 sits, which contains a propellant charge chamber 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 bottom 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 sits a drum 24 for the secondary secondary line 25, which consists of a comparatively long safety line, which is attached at one end to the drum 24 and at the other end to a central piece 26 which is 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 above-mentioned 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 transfer 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 located 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 on 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 which now develop pass through holes in 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 -Pushed launch tube, so it is shot. 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 double throwing 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 has been 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 time corresponds to the sketch A of Fig. 2. As soon as the The secondary line of the secondary line is completely unwound and tensioned, the secondary line ignites the throwing body, which point in time is shown in sketch B of 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 has been fully tensioned, the firing pin 31 strikes 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, the coupling piece 30 breaks, that is to say the connection between the piston rod 29 and the firing pin 31 is released, so that the firing pin 31 strikes forward through the now relaxing spring 32 against the primer 35. 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 piece 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 thus 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 launch site, at a predetermined height above the ground. If the throwing body, as in the exemplary embodiment, is a double body, then the problem is how to operate the double body at a speed of about 150 km / h at a target point, the front body above the ground and the rear body should release a cloud of fog on the ground. Both clouds of fog should mix, i.e., 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 possible pull 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 aforementioned subdivision of the active charge into a spontaneous batch and a batch of points ensures an almost sudden nebulization effect, with a sufficient fog duration, but requires the ignition accuracy of the safety line system described.

Es ist besonders zweckmäßig, die Abschußrohre der Werfereinrichtung als Abschußmagazine gemäß der Patentanmeldung P.... vom gleichen Tage auszubilden.It is particularly expedient to design the launching tubes of the launcher device as launching magazines according to patent application P .... from the same day.

Claims (9)

1. Selbstschutz-Werfereinrichtung, bestehend aus einem am zu schützenden Objekt angebrachten Abschußrohr mit elektrischer Zündvorrichtung am Rohrboden und mit einem in das Abschußrohr eingesetzten Wurfkörper mit einer Treibladung und einer Wirkladung sowie Zündvorrichtungen zum Anzünden der Treibladung und der Wirkladung, dadurch gekennzeichnet, daß die Wirkladungs-Zündvorrichtung einen Schlagbolzen (31) mit Schlagbolzenfeder (32) aufweist und mit dem einen Ende einer mit ihrem anderen Ende am Abschußrohr bzw. einem im Abschußrohr verbleibenden Teil (15) gehaltenen, zum Spannen der Feder (32) und Auslösen des Schlagbolzens (31) dienenden Fangleine (21, 25) verbunden ist, wobei die Fangleine (21, 25) geringfügig kürzer ist als der durch die Treibladung (17) vorgegebenen Schußweite des Wurfkörpers entspricht.1. Self-protection launcher device, consisting of a launch tube attached to the object to be protected with an electrical ignition device on the tube sheet and with a projectile inserted into the launch tube with a propellant charge and an active charge, as well as ignition devices for igniting the propellant charge and the active charge, characterized in that the active charge -Ignition device has a firing pin (31) with firing pin spring (32) and with one end of one with its other end held on the launch tube or a part (15) remaining in the launch tube, for tensioning the spring (32) and triggering the firing pin (31 ) serving safety line (21, 25) is connected, the safety line (21, 25) being slightly shorter than the firing range (17) given by the range of the throwing body. 2. Selbstschutz-Werfereinrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Fangleine aus einem Primärteil (21) und einem Sekundärteil (25) besteht, wobei das Primärteil (21) einerseits an einem am Boden der Wurfgeschoßhülse (10) angeordneten, beim Abschuß des Wurfkörpers mit der Hülse (10) im Abschußrohr verbleibenden Ankerdeckel (15) und andererseits an einem Treibladungsgehäuse (16) befestigt ist, der Sekundärteil (25) der Fangleine einerseits am Treibladungsgehäuse (16) und andererseits an einer mit dem Schlagbolzen (31) verbundenen Kolbenstange (29) befestigt ist und das Treibladungsgehäuse (16) ein vom Ankerdeckel (15) und vom Wirkteil (29, 31, 32, 33, 39) des Wurfgeschosses lösbares Bauelement ist.2. Self-protection launcher device according to claim 1, characterized in that the safety line consists of a primary part (21) and a secondary part (25), the primary part (21) arranged on the one hand on a at the bottom of the projectile sleeve (10) when the Throwing body with the sleeve (10) in the launch tube remaining anchor cover (15) and on the other hand attached to a propellant charge housing (16), the secondary part (25) of the suspension line on the one hand on the propellant charge housing (16) and on the other hand on a piston rod connected to the firing pin (31) (29) is fastened and the propellant charge housing (16) is a component that can be detached from the anchor cover (15) and from the active part (29, 31, 32, 33, 39) of the projectile. 3. Selbstschutz-Werfereinrichtung nach Anspruch 2, dadurch gekennzeichnet, daß der Primärteil (21) der Fangleine aus mehreren, konzentrisch zur Wurfkörper-Längsachse angeordneten Einzelleinen besteht.3. Self-protection throwing device according to claim 2, characterized in that the primary part (21) of the safety line consists of several individual lines arranged concentrically to the longitudinal axis of the throwing body. 4. Selbstschutz-Werfereinrichtung nach Anspruch 2 oder 3, dadurch gekennzeichnet, daß die Kolbenstange (29) mit dem Schlagbolzen (31) mittels eines Kopplungsstücks (30) verbunden ist, das eine Soll-Reißstelle aufweist.4. Self-protection launcher device according to claim 2 or 3, characterized in that the piston rod (29) is connected to the firing pin (31) by means of a coupling piece (30) which has a predetermined breaking point. 5. Selbstschutz-Werfereinrichtung nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß der Wurfkörper eine über eine Anzünd-Zerlegerladung (40) entzündbare Spontan-Nebelladung (39) und eine über ein Verzögerungsstück (37) und eine Anzündladung (38) anzündbare Punkt-Nebelladung enthält.5. Self-protection launcher device according to one of claims 1 to 4, characterized in that the throwing body has a spontaneous mist charge (39) which can be ignited via an ignition-splitter charge (40) and one which can be ignited via a delay piece (37) and an ignition charge (38) Contains point fog charge. 6. Selbstschutz-Werfereinrichtung nach Anspruch 5, dadurch gekennzeichnet, daß sowohl Anzünd-Zerlegerladung (40) als auch das Verzögerungsstück (37) von einer Anzündladung (36) anzündbar sind, die ihrerseits von einem durch den Schlagbolzen (31) beaufschlagbares Zündhütchen (36) entzündbar ist.6. Self-protection launcher device according to claim 5, characterized in that both igniter charge (40) and the delay piece (37) can be ignited by an ignition charge (36), which in turn can be acted upon by a firing pin (31) by the firing pin (31) ) is flammable. 7. Selbstschutz-Werfereinrichtung nach einem der Ansprüche 2 bis 6, dadurch gekennzeichnet, daß an der Befestigungsstelle des Ankerdeckels (15) ein pyrotechnisches Trennelement (22) angeordnet ist, dem ein von den Treibgasen der Treibladung (17) anzündbares Verzögerungsstück (23) vorgeschaltet ist.7. Self-protection launcher device according to one of claims 2 to 6, characterized in that a pyrotechnic separating element (22) is arranged at the fastening point of the anchor cover (15), which is preceded by a delay piece (23) which can be ignited by the propellant gases of the propellant charge (17) is. 8. Selbstschutz-Werfereinrichtung nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß am Wurfgeschoß-Boden das Sekundärteil (13, 14) eines induktiven Zündsystems angeordnet ist.8. Self-protection launcher device according to one of claims 1 to 7, characterized in that the secondary part (13, 14) of an inductive ignition system is arranged on the projectile floor. 9. Selbstschutz-Werfereinrichtung nach einem der Ansprüche 1 bis 8, gekennzeichnet durch eine Luftfeder (44) zur Fangleinendämpfung.9. Self-protection launcher device according to one of claims 1 to 8, characterized by an air spring (44) for cushioning lines.
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

Publications (2)

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

Family

ID=6437408

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92106652A Expired - Lifetime EP0525305B1 (en) 1991-07-31 1992-04-16 Launching device for tank self protection

Country Status (4)

Country Link
US (1) US5272981A (en)
EP (1) EP0525305B1 (en)
CA (1) CA2068399A1 (en)
DE (2) DE4125355C1 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0687885A1 (en) * 1993-12-01 1995-12-20 Konstruktorskoe Bjuro Mashinostroenia Vehicle self-defence system
EP0774642A1 (en) * 1995-11-17 1997-05-21 Giat Industries Dispersing or applicating process of an active material, composition and projectile manufactured according to such a process
FR2741435A1 (en) * 1995-11-17 1997-05-23 Giat Ind Sa Dispersion or application of an active material composition
FR2741434A1 (en) * 1995-11-17 1997-05-23 Giat Ind Sa Dispersion or application of an active material composition
FR2741433A1 (en) * 1995-11-17 1997-05-23 Giat Ind Sa DEVICE FOR LAUNCHING A NON-LETHAL PROJECTILE
FR2914054A1 (en) * 2007-03-19 2008-09-26 Nexter Systems Sa Close base e.g. fixed building, protection device, has secondary expulsion unit that is triggered so as to exclude sub-projectile, when secondary expulsion unit is oriented at relative bearing angle determined before firing
FR2937123A1 (en) * 2008-10-13 2010-04-16 Nexter Munitions Ammunition i.e. heavy caliber artillery ammunition, for controlling active crowd, has projectile with body containing loads assuring non lethal effect, and deployment units that deploy non lethal effect loads in sequence

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4302413C1 (en) * 1991-07-31 1994-03-17 Buck Chem Tech Werke Projector for automatic protection - has missile-arrester line in layers one behind other in axial direction
DE4337680C2 (en) * 1993-11-04 1995-08-24 Buck Chem Tech Werke Two-component smoke projectors
DE4340905C2 (en) * 1993-12-01 1998-12-10 Daimler Benz Aerospace Ag Combating violent persons
FR2930984A1 (en) * 1994-03-15 2009-11-13 Poudres Et Explosifs Snpe Sa S METHOD AND AMMUNITION OF COUNTER-MEASUREMENT BY UNIDIRECTIONAL VISION SCREEN
US5750918A (en) * 1995-10-17 1998-05-12 Foster-Miller, Inc. Ballistically deployed restraining net
DE19543489C1 (en) * 1995-11-22 1997-06-26 Buck Chem Tech Werke Protective device for fast moving objects
DE10226507A1 (en) * 2002-06-14 2003-12-24 Diehl Munitionssysteme Gmbh A smoke
FR2886003B1 (en) * 2005-05-20 2007-08-17 Lacroix Soc E SIMPLIFIED SAFETY TRAINING CARTRIDGE
EP2232191A4 (en) 2007-09-18 2013-03-27 Pepperball Technologies Inc Systems, methods and apparatus for use in distributing irritant powder
ES2392984A1 (en) * 2010-05-10 2012-12-17 Falken, S.A. Multi-pectral hidden artificial (Machine-translation by Google Translate, not legally binding)
CN103486911B (en) * 2013-09-13 2015-04-22 长沙凯维科技有限公司 Single-shot firework base preinstalled with heating resistance wire and corresponding fixing seat
JP6563773B2 (en) * 2015-10-20 2019-08-21 株式会社ダイセル Smoke screen generator

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE146540C (en) *
DE1095713B (en) * 1958-03-27 1960-12-22 Richard Rinker K G A A Zugzuender
DE1275427B (en) * 1962-10-30 1968-08-14 Bock Fa Geb Trigger for fireworks rockets
GB1312444A (en) * 1969-04-23 1973-04-04 Pains Wessex Ltd Pyrotechnic devices
US3930448A (en) * 1972-06-23 1976-01-06 The United States Of America As Represented By The Secretary Of The Navy Rocket-deployed balloon for position marker
WO1984002769A1 (en) * 1983-01-11 1984-07-19 Tulcea Sa Percussion device

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2805622A (en) * 1954-08-09 1957-09-10 John Radtke Rocket missiles
US3726226A (en) * 1971-08-31 1973-04-10 Us Army Universal smoke marking grenade for dry and inundated areas
AT330030B (en) * 1973-02-15 1976-06-10 Urbach Ing Erich LAUNCHER
US4526105A (en) * 1983-07-22 1985-07-02 Herren Jr Thomas W Firing mechanism for projectiles
US4726295A (en) * 1986-05-16 1988-02-23 Aai Corporation Grenade arrangement for screening cloud
CA1311391C (en) * 1988-09-23 1992-12-15 Stephen B. Murray Fuel-air line-charge ordnance neutralizer
US5042390A (en) * 1989-10-18 1991-08-27 Hughes Aircraft Company Apparatus for lauching umbilical-guided missiles

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE146540C (en) *
DE1095713B (en) * 1958-03-27 1960-12-22 Richard Rinker K G A A Zugzuender
DE1275427B (en) * 1962-10-30 1968-08-14 Bock Fa Geb Trigger for fireworks rockets
GB1312444A (en) * 1969-04-23 1973-04-04 Pains Wessex Ltd Pyrotechnic devices
US3930448A (en) * 1972-06-23 1976-01-06 The United States Of America As Represented By The Secretary Of The Navy Rocket-deployed balloon for position marker
WO1984002769A1 (en) * 1983-01-11 1984-07-19 Tulcea Sa Percussion device

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0687885A1 (en) * 1993-12-01 1995-12-20 Konstruktorskoe Bjuro Mashinostroenia Vehicle self-defence system
EP0687885A4 (en) * 1993-12-01 1996-12-20 Kb Mash Vehicle self-defence system
EP0774642A1 (en) * 1995-11-17 1997-05-21 Giat Industries Dispersing or applicating process of an active material, composition and projectile manufactured according to such a process
FR2741435A1 (en) * 1995-11-17 1997-05-23 Giat Ind Sa Dispersion or application of an active material composition
FR2741434A1 (en) * 1995-11-17 1997-05-23 Giat Ind Sa Dispersion or application of an active material composition
FR2741433A1 (en) * 1995-11-17 1997-05-23 Giat Ind Sa DEVICE FOR LAUNCHING A NON-LETHAL PROJECTILE
EP0779495A1 (en) * 1995-11-17 1997-06-18 Giat Industries Device for launching a non lethal projectile
FR2914054A1 (en) * 2007-03-19 2008-09-26 Nexter Systems Sa Close base e.g. fixed building, protection device, has secondary expulsion unit that is triggered so as to exclude sub-projectile, when secondary expulsion unit is oriented at relative bearing angle determined before firing
FR2937123A1 (en) * 2008-10-13 2010-04-16 Nexter Munitions Ammunition i.e. heavy caliber artillery ammunition, for controlling active crowd, has projectile with body containing loads assuring non lethal effect, and deployment units that deploy non lethal effect loads in sequence

Also Published As

Publication number Publication date
US5272981A (en) 1993-12-28
DE59201177D1 (en) 1995-02-23
CA2068399A1 (en) 1993-02-01
DE4125355C1 (en) 1993-01-28
EP0525305B1 (en) 1995-01-11

Similar Documents

Publication Publication Date Title
EP0525305B1 (en) Launching device for tank self protection
EP0164732B1 (en) Apparatus for generating decoy clouds, in particular those emitting ir radiation
DE2809497A1 (en) LOCKING CONTAINER FOR THE DUEPPELUNG OF STEERING ARMS
DE2907308C2 (en) Floor with at least one pushable daughter floor
DE69129815T2 (en) Penetrator ammunition for targets with high mechanical resistance
DE903320C (en) Delay device for explosive charges
DE1703557A1 (en) Projectile with a payload to be released at a certain point in the flight path
EP0656521B1 (en) Smoke charge having two components
DE3806731A1 (en) SUBMUNITION ACTIVE UNIT, FLECHETTES HEAD OF HEAD AND FLECHETTES DAFUER
DE3421692C2 (en) Method and projectile for creating an IR decoy
DE69709852T2 (en) Grenade for grenade launchers
EP1166033B1 (en) Electronically and mechanically-operated ignition delay for cartridge-type pyrotechnic decoy flare ammunition
DE4105271C1 (en)
DE3112191A1 (en) GROUND BLASTING, ESPECIALLY FOR RIFLE GRENADES
DE2427680A1 (en) MOBILE LAUNCH DEVICE FOR TANK-BREAKING BODIES
EP0913663B1 (en) Pyrotechnic impact igniter
DE69405376T2 (en) Anti-tank projectile and ammunition provided with such a projectile
DE647283C (en) Impact fuse, especially for projectiles and hand grenades
DE382708C (en) Whisker
DE3534197C2 (en)
DE1578132C1 (en) Floor with a large number of independent inner floors
DE51465C (en) Projectile or torpedo with explosive charge and electric detonator
DE1678206A1 (en) bullet
DE913753C (en) Device for remote ignition of the ignition charge surrounded by the explosive charge of a projectile by means of an auxiliary charge
DE2719977A1 (en) Aerosol explosion for civil or military use - produced by one initiating charge exploded within aerosol cloud

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

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

17P Request for examination filed

Effective date: 19930302

17Q First examination report despatched

Effective date: 19940615

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

ITF It: translation for a ep patent filed
ET Fr: translation filed
GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19950118

REF Corresponds to:

Ref document number: 59201177

Country of ref document: DE

Date of ref document: 19950223

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

Ref country code: LI

Effective date: 19950430

Ref country code: CH

Effective date: 19950430

Ref country code: BE

Effective date: 19950430

BERE Be: lapsed

Owner name: BUCK WERKE G.M.B.H. & CO.

Effective date: 19950430

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

Ref country code: NL

Effective date: 19951101

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: FR

Effective date: 19951229

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 19951101

26N No opposition filed
REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

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

Ref country code: GB

Payment date: 19960415

Year of fee payment: 5

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

Ref country code: DE

Payment date: 19960426

Year of fee payment: 5

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

Ref country code: GB

Effective date: 19970416

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19970416

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

Ref country code: DE

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

Effective date: 19980101

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

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050416