EP0152516A2 - Mine - Google Patents

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Publication number
EP0152516A2
EP0152516A2 EP84108581A EP84108581A EP0152516A2 EP 0152516 A2 EP0152516 A2 EP 0152516A2 EP 84108581 A EP84108581 A EP 84108581A EP 84108581 A EP84108581 A EP 84108581A EP 0152516 A2 EP0152516 A2 EP 0152516A2
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EP
European Patent Office
Prior art keywords
ignition
signal
mine according
mine
flying object
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Granted
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EP84108581A
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German (de)
French (fr)
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EP0152516A3 (en
EP0152516B1 (en
Inventor
Hermann Grosch
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Atlas Elektronik GmbH
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Fried Krupp AG
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Priority to AT84108581T priority Critical patent/ATE54747T1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B23/00—Land mines ; Land torpedoes
    • F42B23/10—Land mines ; Land torpedoes anti-personnel
    • F42B23/16—Land mines ; Land torpedoes anti-personnel of missile type, i.e. all kinds of mines launched for detonation after ejection from ground
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C11/00—Electric fuzes
    • F42C11/001—Electric circuits for fuzes characterised by the ammunition class or type
    • F42C11/007—Electric circuits for fuzes characterised by the ammunition class or type for land mines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/06—Proximity fuzes; Fuzes for remote detonation operated by sound waves

Definitions

  • the invention relates to a mine of the type mentioned in the preamble of claim 1.
  • Mines are a long-known and successfully used stationary (land mine) or quasi-stationary (sea mine) weapon to protect the area against intrusion of individual enemy objects or enemy combat groups. Because of their constructive design, however, mines can only be used against objects that move on the surface of the ground or the sea, i.e. at a predetermined level. However, they are completely ineffective for objects flying over the level level with a greater or lesser distance, such as low-flying helicopters or the like.
  • Landmines also have the additional disadvantage that they are ignited by the pressure of rolling vehicles and can only destroy the vehicle from below. They are therefore essentially ineffective against vehicles with heavy ground armor, such as battle tanks or mine clearance vehicles.
  • the invention has for its object to provide mines of the type mentioned, which also sufficiently secure the air space above its station level up to a relevant maximum height.
  • the mine according to the invention combines the advantage of very low manufacturing costs with the effectiveness against helicopters flying in the field. Its preferably acoustic location device measures the helicopter at an early stage and adjusts the detonation height of the mine. So As soon as the helicopter enters the mine, a detonation body is ejected vertically and detonated at approximately the helicopter's flight level. The explosive charge, which preferably consists of fragmentation ammunition, will then reliably destroy the helicopter or at least damage it until it becomes unable to fly.
  • the mine according to the invention is equally advantageous against vehicles with heavy ground armor, eg. B. tanks or mine clearance vehicles can be used.
  • the detonation body is ejected when the vehicle enters the effective area of the mine and explodes at a predetermined floor height directly in front of the vehicle, so in a region in which the vehicle can easily be destroyed or rendered unusable.
  • z. B. destroy the optical devices of a modern battle tank, so that it fails for combat purposes.
  • the mine according to the invention also has the advantage of being able to be installed quickly, in particular if the installation is carried out by firing.
  • the mine shown schematically in longitudinal section in FIG. 1, has a housing 10 designed for firing with a barrel weapon with a housing cover 11 that can be detached.
  • a detonator capsule 12 which can be ejected vertically from the housing 10 by means of a propellant charge 13, which is ignited by a propellant charge igniter 14, with the housing cover 11 being detached.
  • the detonator capsule 12 encloses a fragmentation ammunition 15 and an approximately centrally embedded explosive charge 16 with an explosive charge detonator 17.
  • the explosive charge detonator 17 is designed as a time detonator with ignition timer 18, ignition time adjuster 19 and ignition trigger 20 actuated by ignition timer 18.
  • a receiver 21 of a locating device 42 for detecting and measuring an approaching object e.g. B. a flying object with low airspeed, as it is formed by a helicopter.
  • the output of the receiver 21 is connected to an evaluation unit 22 for processing the received signals.
  • the evaluation unit 22, which is shown in the block diagram in FIG. 2, is designed in such a way that, on the one hand, it sets a response time for the ignition timing adjuster 19 from the received signals and on the other hand, an ignition signal for the propellant charge igniter 14 and an activation signal for the ignition timer 18 are generated.
  • the receiver 21 of the acoustic locating device 42 which is passive in the exemplary embodiment, has four electroacoustic transducers 23 to 26 which are arranged at each corner of a square lying in a horizontal plane and form two dipoles aligned at right angles to one another.
  • the two dipoles can also be formed by only three electroacoustic transducers, which are then arranged in the corner points of an isosceles, right-angled triangle lying in the horizontal plane.
  • the electroacoustic transducers 23 to 26 are designed as microphones with all-round characteristics.
  • a small parachute 27 (FIG. 1) is attached to the housing 10 in the case of mines which are laid by firing, which ensures the corresponding alignment of the housing 10 when it hits the ground. Appropriate shaping of the housing 10 can have a supporting effect.
  • the latter has an flight altitude estimation device 28 and an ignition time calculator 29.
  • the flight altitude estimating device 28 determines at least approximately the flight altitude h Z of an approaching flying object from the output signals of the receiver 21, and the ignition time calculator 29 calculates the estimated flight altitude h Z and the
  • Ejection speed v of the detonator 12 according to its rise time t Z and derives therefrom a setting time signal which is at the input of the ignition time adjuster 19 connected to the ignition time calculator 29.
  • the ignition time of the ignition timer 18 is set in accordance with this setting time signal.
  • the flight altitude estimation device 28 has a circuit arrangement 32 for determining the elevation angle ⁇ to the flying object and for determining at least one characteristic frequency f of the flying object.
  • a circuit arrangement which also has the azimuth angle can determine to the flying object, but which is not used here, is described in detail in DE-OS 30 17 797, so that it need not be discussed in more detail here.
  • This circuit arrangement 32 is followed by a flight altitude computer 33, to which, on the one hand, the elevation angle ⁇ and, on the other hand, a selected frequency f from the frequency spectrum of the measured flying object are fed both immediately and after time differentiation in a differentiator 34 or 35.
  • the flight altitude calculator 33 uses this to calculate the flight altitude h Z of the measured target in accordance with
  • the output of the circuit arrangement 32 leading to the elevation angle ⁇ for frequency and elevation angle determination is connected to a computing element 36, which calculates the tangent of the Elevation angle value ⁇ calculated.
  • the output of the arithmetic element 36 is connected to a multiplier 37, whose other input is connected to the output of the flight altitude computer 33.
  • the predetermined value A max is calculated according to the radial range of the fragmentation ammunition 15 of the detonator capsule 12. If the distance value A output by the multiplier 37 is smaller than the predetermined value A max, the comparator 38 outputs an output signal which is converted by means of a pulse shaper 39 into the ignition signal for the propellant charge igniter 14 and into the activation signal at the start of the ignition timer 18.
  • the output signal of the pulse shaper 39 only reaches the time igniter 18 and propellant charge detonator 14 when the flight altitude h calculated by the flight altitude computer 33 Z is smaller than the maxi male height h max of the detonator capsule 12.
  • the pulse former 39 is followed by a gate element 30, the control input of which is connected to the output of a comparator 31.
  • the comparator 31 is supplied on the one hand with the maximum climbing height h max of the detonator 12 and, on the other hand, with the connecting height to the flight altitude computer 33, the flight height h Z of the flying object detected by the receiver 21.
  • the mine can be given selection properties for flying objects.
  • the frequency spectrum of the measured flying object which is anyway determined in the circuit arrangement 32 for determining the frequency and elevation angle, is fed to the classification device 40.
  • the detected frequency spectrum is compared with the spectrum of a flying object, the mine of which is to be used exclusively for fighting.
  • the classification device 40 only emits a control signal if the detected frequency spectrum corresponds to the known one. This control signal is fed to an input of an AND gate 41 to be provided, at the other input of which the output signal of the comparator 31 is then applied.
  • the output of the AND gate 41 is connected to the control input of the gate gate 30.
  • An ignition signal or an activation signal therefore only reaches the propellant charge igniter 14 or the ignition timer 19 when the gate member 30 is open, ie the measured flying object has been classified as a target to be combated and na of course if its flight height h Z is less than the maximum height h max of the detonator capsule 12.
  • the evaluation unit 22 When using the mine against ground vehicles, the evaluation unit 22 is considerably simplified.
  • the ignition timer 18 is always set to a constant ignition time, so that the ignition time calculator 29 and also the flight altitude calculator 33 are omitted.
  • Receiver 21 and evaluation unit 22 must, however, be designed so that the distance of the ground vehicle from the mine can be determined.
  • seismic sensors and a corresponding configuration of the evaluation unit 22 as described in GB-PS 1515447 or DE-OS 32 04 874 would be advantageous as receivers 21.
  • the comparator 38 will emit an output signal if the measured distance falls below a predetermined minimum distance.
  • the ignition timer 19 is then activated and the propellant charge igniter 14 is triggered.
  • the detonator 12 is ejected vertically at the initial speed v o and detonates at a predetermined level after the constant ignition time has elapsed.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)

Abstract

1. A mine having : a casing (10) ; a detonating cap (12) which can be ejected from the casing (10) and contains an explosive charge (16) and an explosive charge igniting device taking the form of a delay-action cap with an ignition point mechanism (18) and an ignition triggering device (19) actuated thereby ; and a propellant charge (13) having a propellant charge ignition device (14) for the substantially vertical ejection of the detonating cap (12) and a sensor for detecting objects from whose detection the activation of the propellant charge ignition device (14) and the explosive charge ignition device (17) is derived, characterized in that the explosive charge ignition device (17) has an ignition point adjuster (19) for adjusting the ignition point in the ignition point mechanism (18), and the sensor is formed by a locating device (42) having at least one receiver (21) and a connected evaluating unit (22) so constructed that it determines from the signals received the ignition point for the propellant charge ignition device (14) and the explosive charge ignition device (17) and delivers corresponding control signals thereto.

Description

Die Erfindung betrifft eine Mine der im Oberbegriff des Anspruchs 1 genannten Art.The invention relates to a mine of the type mentioned in the preamble of claim 1.

Minen sind ein seit langem bekanntes und erfolgreich angewendetes stationäres (Landminen) bzw. quasistationäres (Seeminen) Kampfmittel zur Gebietssicherung gegen Eindringen von einzelnen Feindobjekten oder gegnerischen Kampfverbänden. Aufgrund ihrer konstruktiven Gestaltung können Minen jedoch nur gegen Objekte eingesetzt werden, die sich auf der Boden- oder Meeresoberfläche, also auf einer vorgegebenen Niveauebene bewegen. Für die Niveauebene mit mehr oder weniger großem Abstand überfliegende Objekte, wie tieffliegende Hubschrauber oder dergl., sind sie jedoch völlig unwirksam.Mines are a long-known and successfully used stationary (land mine) or quasi-stationary (sea mine) weapon to protect the area against intrusion of individual enemy objects or enemy combat groups. Because of their constructive design, however, mines can only be used against objects that move on the surface of the ground or the sea, i.e. at a predetermined level. However, they are completely ineffective for objects flying over the level level with a greater or lesser distance, such as low-flying helicopters or the like.

Landminen haben zudem noch den zusätzlichen Nachteil, daß sie vom Druck sie überrollender Fahrzeuge gezündet werden und das Fahrzeug nur von unten her zerstören können. Gegen Fahrzeuge mit starker Bodenpanzerung, wie Kampfpanzer oder Minenräumfahrzeuge, sind sie daher im wesentlichen wirkungslos.Landmines also have the additional disadvantage that they are ignited by the pressure of rolling vehicles and can only destroy the vehicle from below. They are therefore essentially ineffective against vehicles with heavy ground armor, such as battle tanks or mine clearance vehicles.

Der Erfindung liegt die Aufgabe zugrunde, Minen der eingangs genannten Art zu schaffen, die auch den oberhalb ihrer Stationierungsebene befindlichen Luftraum bis zu einer relevanten Maximalhöhe ausreichend zuverlässig sichern.The invention has for its object to provide mines of the type mentioned, which also sufficiently secure the air space above its station level up to a relevant maximum height.

Die Aufgabe ist bei einer Mine der im Oberbegriff des Anspruchs 1 angegebenen Gattung erfindungsgemäß durch die Merkmale im Kennzeichenteil des Anspruchs 1 gelöst:

  • Die erfindungsgemäße Mine hat den wesentlichen Vorteil, ein preiswertes stationäres Kampfmittel zur Hubschrauberabwehr darzustellen. Die bisher hierfür eingesetzten Abwehrwaffen, wie endphasengelenkte Flugkörper, Hubschrauberabwehrhubschrauber, oder konventionelle Rohrwaffen, wie Flak, Fliegerfäuste und dergl., befriedigen entweder aus Gründen der geringen Erfolgswahrscheinlichkeit oder aus Kostengründen nicht. Gelenkte Flugkörper sind sehr komplex und daher sehr teuer. Konventionelle Rohrwaffen hingegen sind in der Regel wenig wirkungsvoll, da Hubschrauber sich tieffliegend unter Ausnutzung der vom Gelände gegebenen Deckungsmöglichkeiten dem Zielgebiet nähern, damit einerseits für die Rohrwaffe kein ausreichend gutes Ziel bieten und andererseits nicht frühzeitig geortet werden können, was für ein erfolgreiches Einsetzen der Rohrwaffe unbedingt erforderlich wäre.
The object is achieved in a mine of the type specified in the preamble of claim 1 according to the invention by the features in the characterizing part of claim 1:
  • The mine according to the invention has the essential advantage of being an inexpensive stationary weapon for helicopter defense. The defense weapons used for this purpose, such as end-phase guided missiles, helicopter defense helicopters, or conventional barrel weapons, such as anti-aircraft guns, fists and the like, are unsatisfactory either because of the low probability of success or for reasons of cost. Guided missiles are very complex and therefore very expensive. Conventional tube weapons, on the other hand, are generally not very effective, since helicopters approach the target area using the available cover, so that on the one hand they do not offer a sufficiently good target for the tube weapon and, on the other hand, they cannot be located early, what a successful use of the tube weapon would be absolutely necessary.

Die erfindungsgemäße Mine hingegen vereinigt den Vorteil der sehr geringen Herstellungskosten mit der Wirksamkeit gegen in Geländedeckung fliegende Hubschrauber. Ihre vorzugsweise akustische Ortungsvorrichtung vermißt frühzeitig den Hubschrauber und stellt die Detonationshöhe der Mine ein. Sobald der Hubschrauber in den Wirkungsbereich der Mine eindringt, wird ein Detonationskörper vertikal ausgestoßen und in etwa in Flughöhe des Hubschraubers zur Detonation gebracht. Die vorzugsweise aus Splittermunition bestehende Sprengladung wird dann den Hubschrauber sicher zerstören oder zumindest bis zur Flugunfähigkeit beschädigen.The mine according to the invention, on the other hand, combines the advantage of very low manufacturing costs with the effectiveness against helicopters flying in the field. Its preferably acoustic location device measures the helicopter at an early stage and adjusts the detonation height of the mine. So As soon as the helicopter enters the mine, a detonation body is ejected vertically and detonated at approximately the helicopter's flight level. The explosive charge, which preferably consists of fragmentation ammunition, will then reliably destroy the helicopter or at least damage it until it becomes unable to fly.

Die erfindungsgemäße Mine ist aber gleich vorteilhaft gegen Fahrzeuge mit starker Bodenpanzerung, z. B. Panzer oder Minenräumfahrzeuge, einsetzbar. Auch in diesem Fall wird der Detonationskörper bei Eindringen des Fahrzeugs in den Wirkbereich der Mine ausgestoßen und explodiert in vorgegebener Bodenhöhe unmittelbar vor dem Fahrzeug, damit in einer Region, in welcher das Fahrzeug leicht zerstört oder unbrauchbar gemacht werden kann. Auf diese Weise lassen sich z. B. die optischen Einrichtungen eines modernen Kampfpanzers zerstören, so daß dieser für den Kampfeinsatz ausfällt.The mine according to the invention is equally advantageous against vehicles with heavy ground armor, eg. B. tanks or mine clearance vehicles can be used. In this case too, the detonation body is ejected when the vehicle enters the effective area of the mine and explodes at a predetermined floor height directly in front of the vehicle, so in a region in which the vehicle can easily be destroyed or rendered unusable. In this way, z. B. destroy the optical devices of a modern battle tank, so that it fails for combat purposes.

Die erfindungsgemäße Mine hat zudem den Vorteil, schnell verlegt werden zu können, insbesondere wenn die Verlegung durch Verschießen erfolgt.The mine according to the invention also has the advantage of being able to be installed quickly, in particular if the installation is carried out by firing.

Ausführungsformen der Erfindung mit vorteilhaften Ausgestaltungen und Weiterbildungen sind Gegenstand der weiteren Ansprüche.Embodiments of the invention with advantageous refinements and developments are the subject of the further claims.

Die Erfindung ist anhand eines in der Zeichnung dargestellten Ausführungsbeispiels beschrieben. Es zeigen:

  • Fig. 1 einen Längsschnitt einer Mine, schematisch dargestellt,
  • Fig. 2 ein Blockschaltbild einer passiven akustischen Ortungsvorrichtung der Mine in Fig. 1.
The invention is described with reference to an embodiment shown in the drawing. Show it:
  • 1 shows a longitudinal section of a mine, shown schematically,
  • FIG. 2 is a block diagram of a passive acoustic location device of the mine in FIG. 1.

Die in Fig. 1 im Längsschnitt schematisch dargestellte Mine weist ein zum Verschießen mit einer Rohrwaffe ausgebildetes Gehäuse 10 mit absprengbarem Gehäusedeckel 11 auf. Im Inneren des Gehäuses 10 befindet sich eine Sprengkapsel 12, die mittels einer Treibladung 13,.die von einem Treibladungszünder 14 gezündet wird, unter Absprengung des Gehäusedeckels 11 vertikal aus dem Gehäuse 10 ausgestoßen werden kann. Die Sprengkapsel 12 umschließt eine Splittermunition 15 und eine etwa zentral eingebettete Sprengladung 16 mit Sprengladungszünder 17. Der Sprengladungszünder 17 ist als Zeitzünder mit Zündzeitwerk 18, Zündzeiteinsteller 19 und von dem Zündzeitwerk 18 betätigten Zündauslöser 20 ausgebildet.The mine, shown schematically in longitudinal section in FIG. 1, has a housing 10 designed for firing with a barrel weapon with a housing cover 11 that can be detached. In the interior of the housing 10 there is a detonator capsule 12, which can be ejected vertically from the housing 10 by means of a propellant charge 13, which is ignited by a propellant charge igniter 14, with the housing cover 11 being detached. The detonator capsule 12 encloses a fragmentation ammunition 15 and an approximately centrally embedded explosive charge 16 with an explosive charge detonator 17. The explosive charge detonator 17 is designed as a time detonator with ignition timer 18, ignition time adjuster 19 and ignition trigger 20 actuated by ignition timer 18.

Unmittelbar unter dem Gehäusedeckel 11 ist ein Empfänger 21 einer Ortungsvorrichtung 42 zur Erfassung und Vermessung eines sich annähernden Objektes, z. B. eines Flugobjektes mit niedriger Fluggeschwindigkeit, wie es von einem Hubschrauber gebildet wird, angeordnet. Der Ausgang des Empfängers 21 ist mit einer Auswerteeinheit 22 zur Verarbeitung der Empfangssignale verbunden. Die Auswerteeinheit 22, die in Fig. 2 im Blockschaltbild dargestellt ist, ist derart ausgebildet, daß sie aus den Empfangssignalen einerseits eine Einstellzeit für den Zündzeiteinsteller 19 vorgibt und andererseits ein Zündsignal für den Treibladungszünder 14 und ein Aktivierungssignal für das Zündzeitwerk 18 erzeugt.Immediately below the housing cover 11 is a receiver 21 of a locating device 42 for detecting and measuring an approaching object, e.g. B. a flying object with low airspeed, as it is formed by a helicopter. The output of the receiver 21 is connected to an evaluation unit 22 for processing the received signals. The evaluation unit 22, which is shown in the block diagram in FIG. 2, is designed in such a way that, on the one hand, it sets a response time for the ignition timing adjuster 19 from the received signals and on the other hand, an ignition signal for the propellant charge igniter 14 and an activation signal for the ignition timer 18 are generated.

Der Empfänger 21 der im Ausführungsbeispiel passiven akustischen Ortungsvorrichtung 42 weist vier elektroakustische Wandler 23 bis 26 auf, die an jeweils einer Ecke eines in einer Horizontalebene liegenden Quadrats angeordnet sind und zwei rechtwinklig zueinander ausgerichtete Dipole bilden. Die beiden Dipole können aber ebenfalls von nur drei elektroakustischen Wandlern gebildet werden, die dann in den Eckpunkten eines in der Horizontalebene liegenden gleichschenkligen, rechtwinkligen Dreiecks angeordnet werden. Die elektroakustischen Wandler 23 bis 26 sind als Mikrophone mit Rundumcharakteristik ausgebildet. Um die erforderliche horizontale Ausrichtung der elektroakustischen Wandler zu erhalten, ist bei Minen, die durch Verschießen verlegt werden, am Gehäuse 10 ein kleiner Fallschirm 27 (Fig. 1) befestigt, der die entsprechende Ausrichtung des Gehäuses 10 beim Auftreffen auf dem Boden sicherstellt. Eine entsprechende Formgebung des Gehäuses 10 kann dabei unterstützend wirken.The receiver 21 of the acoustic locating device 42, which is passive in the exemplary embodiment, has four electroacoustic transducers 23 to 26 which are arranged at each corner of a square lying in a horizontal plane and form two dipoles aligned at right angles to one another. However, the two dipoles can also be formed by only three electroacoustic transducers, which are then arranged in the corner points of an isosceles, right-angled triangle lying in the horizontal plane. The electroacoustic transducers 23 to 26 are designed as microphones with all-round characteristics. In order to obtain the required horizontal alignment of the electroacoustic transducers, a small parachute 27 (FIG. 1) is attached to the housing 10 in the case of mines which are laid by firing, which ensures the corresponding alignment of the housing 10 when it hits the ground. Appropriate shaping of the housing 10 can have a supporting effect.

Wie aus der schematischen Darstellung der Auswerteeinheit 22 in Fig. 2 hervorgeht, weist diese eine Flughöhen-Schätzvorrichtung 28 und einen Zündzeitrechner 29 auf. Die Flughöhen-Schätzvorrichtung 28 bestimmt aus den Ausgangssignalen des Empfängers 21 zumindest annähernd die Flughöhe hZ eines sich annähernden Flugobjekts, und der Zündzeitrechner 29 errechnet aus der geschätzten Flughöhe hZ und derAs can be seen from the schematic illustration of the evaluation unit 22 in FIG. 2, the latter has an flight altitude estimation device 28 and an ignition time calculator 29. The flight altitude estimating device 28 determines at least approximately the flight altitude h Z of an approaching flying object from the output signals of the receiver 21, and the ignition time calculator 29 calculates the estimated flight altitude h Z and the

Ausstoßgeschwindigkeit v der Sprengkapsel 12 deren Steigzeit tZ gemäß

Figure imgb0001
und leitet daraus ein Einstellzeitsignal ab, das an dem Eingang des mit dem Zün.dzeitrechner·29 verbundenen Zündzeiteinstellers 19 liegt. Entsprechend diesem Einstellzeitsignal wird die Zündzeit des Zündzeitwerks 18 eingestellt.Ejection speed v of the detonator 12 according to its rise time t Z
Figure imgb0001
 and derives therefrom a setting time signal which is at the input of the ignition time adjuster 19 connected to the ignition time calculator 29. The ignition time of the ignition timer 18 is set in accordance with this setting time signal.

Die Flughöhen-Schätzvorrichtung 28 weist eine Schaltungsanordnung 32 zur Bestimmung des Elevationswinkels α zum Flugobjekt und zur Bestimmung mindestens einer charakteristischen Frequenz f des Flugobjekts auf. Eine solche Schaltungsanordnung, die zudem noch den Azimutwinkel

Figure imgb0002
zum Flugobjekt bestimmen kann, der jedoch hier nicht gebraucht wird, ist in der DE-OS 30 17 797 ausführlich beschrieben, so daß hier nicht näher darauf eingegangen zu werden braucht. Dieser Schaltungsanordnung 32 ist ein Flughöhenrechner 33 nachgeschaltet, dem einerseits der Elevationswinkel αund andererseits eine ausgewählte Frequenz f aus dem Frequenzspektrum des vermessenen Flugobjekts jeweils sowohl unmittelbar als auch nach zeitlicher Differenzierung in einem Differenzierglied 34 bzw. 35 zugeführt sind. Der Flughöhenrechner 33 berechnet daraus die Flughöhe hZ des vermessenen Ziels gemäß
Figure imgb0003
 The flight altitude estimation device 28 has a circuit arrangement 32 for determining the elevation angle α to the flying object and for determining at least one characteristic frequency f of the flying object. Such a circuit arrangement, which also has the azimuth angle
Figure imgb0002
can determine to the flying object, but which is not used here, is described in detail in DE-OS 30 17 797, so that it need not be discussed in more detail here. This circuit arrangement 32 is followed by a flight altitude computer 33, to which, on the one hand, the elevation angle α and, on the other hand, a selected frequency f from the frequency spectrum of the measured flying object are fed both immediately and after time differentiation in a differentiator 34 or 35. The flight altitude calculator 33 uses this to calculate the flight altitude h Z of the measured target in accordance with
Figure imgb0003

Zur Erzeugung des Zündsignals für den Treibladungszünder 14 und dem Aktivierungssignal für das Zündzeitwerk 18, das das auf Zündzeit eingestellte Zündzeitwerk 19 startet, ist der den Elevationswinkel α führende Ausgang der Schaltungsanordnung 32 zur Frequenz- und Elevationswinkelbestimmung mit einem Rechenglied 36 verbunden, das den Tangens des Elevationswinkelwertes α berechnet. Der Ausgang des Rechengliedes 36 ist mit einem Multiplizierer 37 verbunden, der mit seinem anderen Eingang an dem Ausgang des Flughöhenrechners 33 angeschlossen ist. Der Multiplizierer 37 berechnet den Abstand A=hZ-tanα. der Vertikalprojektion des vermessenen Flugobjektes auf die Ebene, in welcher der Empfänger 21 angeordnet ist, zu letzterem. In einem Komparator 38 wird dieser Wert mit einem maximal vorgegebenen Wert Amax verglichen. Der vorgegebene Wert Amax wird nach der radialen Reichweite der Splittermunition 15 der Sprengkapsel 12 berechnet. Ist der vom Multiplizierer 37 ausgegebene Abstandswert A kleiner als der vorgegebene Wert A max so gibt der Komparator 38 ein Ausgangssignal aus, das mittels eines Impulsformers 39 in das Zündsignal für den Treibladungszünder 14 und in das Aktivierungssignal zum Start des Zündzeitwerkes 18 umgewandelt wird.In order to generate the ignition signal for the propellant charge igniter 14 and the activation signal for the ignition timer 18, which starts the ignition timer 19 set to ignition time, the output of the circuit arrangement 32 leading to the elevation angle α for frequency and elevation angle determination is connected to a computing element 36, which calculates the tangent of the Elevation angle value α calculated. The output of the arithmetic element 36 is connected to a multiplier 37, whose other input is connected to the output of the flight altitude computer 33. The multiplier 37 calculates the distance A = h Z -tanα. the vertical projection of the measured flying object onto the plane in which the receiver 21 is arranged, to the latter. This value is compared in a comparator 38 with a maximum predetermined value A max . The predetermined value A max is calculated according to the radial range of the fragmentation ammunition 15 of the detonator capsule 12. If the distance value A output by the multiplier 37 is smaller than the predetermined value A max, the comparator 38 outputs an output signal which is converted by means of a pulse shaper 39 into the ignition signal for the propellant charge igniter 14 and into the activation signal at the start of the ignition timer 18.

Um die Mine nicht bei zu hoch fliegenden Zielen, deren Flughöhe über der maximalen Steighöhe der Sprengkapsel 12 liegt, nutzlos ansprechen zu lassen, gelangt das Ausgangssignal des Impulsformers 39 nur dann an Zeitzündwerk 18 und Treibladungszünder 14, wenn die von dem Flughöhenrechner 33 berechnete Flughöhe hZ kleiner ist als die maximale Steighöhe hmax der Sprengkapsel 12. Hierzu ist dem Impulsformer 39 ein Torglied 30 nachgeschaltet, dessen Steuereingang mit dem Ausgang eines Komparators 31 verbunden ist. Dem Komparator 31 ist einerseits die maximale Steighöhe hmax der Sprengkapsel 12 und andererseits über eine Verbindungsleitung zum Flughöhenrechner 33 die Flughöhe hZ des vom Empfänger 21 erfaßten Flugobjekts zugeführt.So that the mine does not respond uselessly to targets flying too high, whose flight altitude is above the maximum climbing height of the detonator capsule 12, the output signal of the pulse shaper 39 only reaches the time igniter 18 and propellant charge detonator 14 when the flight altitude h calculated by the flight altitude computer 33 Z is smaller than the maxi male height h max of the detonator capsule 12. For this purpose, the pulse former 39 is followed by a gate element 30, the control input of which is connected to the output of a comparator 31. The comparator 31 is supplied on the one hand with the maximum climbing height h max of the detonator 12 and, on the other hand, with the connecting height to the flight altitude computer 33, the flight height h Z of the flying object detected by the receiver 21.

Mit Hilfe einer Klassifizierungsvorrichtung 40 kann der Mine Selektionseigenschaft für Flugobjekte verliehen werden. Hierzu wird das in der Schaltungsanordnung 32 zur Frequenz- und Elevationswinkelbestimmung ohnehin ermittelte Frequenzspektrum des vermessenen Flugobjektes der Klassifizierungsvorrichtung 40 zugeführt. Hier wird das detektierte Frequenzspektrum mit dem Spektrum eines Flugobjektes verglichen, zu dessen ausschließlicher Bekämpfung die Mine verwendet werden soll. Nur wenn das detektierte Frequenzspektrum mit dem bekannten übereinstimmt, gibt die Klassifizierungsvorrichtung 40 ein Steuersignal ab. Dieses-Steuersignal wird einem Eingang eines dann vorzusehenden AND-Gliedes 41 zugeführt, an dessen anderem Eingang dann das Ausgangssignal des Komparators 31 liegt. Der Ausgang des AND-Gliedes 41 ist mit dem Steuereingang des Torgliedes 30 verbunden. Ein Zündsignal bzw. ein Aktivierungssignal gelangt daher an den Treibladungszünder 14 bzw. an das Zündzeitwerk 19 nur dann, wenn das Torglied 30 geöffnet ist, das vermessene Flugobjekt also als ein zu bekämpfendes Ziel klassifiziert worden ist und natürlich wenn dessen Flughöhe hZ kleiner ist als die maximale Steighöhe h max der Sprengkapsel 12.With the aid of a classification device 40, the mine can be given selection properties for flying objects. For this purpose, the frequency spectrum of the measured flying object, which is anyway determined in the circuit arrangement 32 for determining the frequency and elevation angle, is fed to the classification device 40. Here the detected frequency spectrum is compared with the spectrum of a flying object, the mine of which is to be used exclusively for fighting. The classification device 40 only emits a control signal if the detected frequency spectrum corresponds to the known one. This control signal is fed to an input of an AND gate 41 to be provided, at the other input of which the output signal of the comparator 31 is then applied. The output of the AND gate 41 is connected to the control input of the gate gate 30. An ignition signal or an activation signal therefore only reaches the propellant charge igniter 14 or the ignition timer 19 when the gate member 30 is open, ie the measured flying object has been classified as a target to be combated and na of course if its flight height h Z is less than the maximum height h max of the detonator capsule 12.

Bei Einsatz der Mine gegen Bödenfahrzeuge vereinfacht sich die Auswerteeinheit 22 erheblich. Hier wird das Zündzeitwerk 18 immer auf eine konstante Zündzeit eingestellt, sodaß der Zündzeitrechner 29 und auch der Flughöhenrechner 33 entfallen. Empfänger 21 und Auswerteeinheit 22 müssen allerdings so ausgebildet sein, daß die Entfernung des Bodenfahrzeuges von der Mine ermittelt werden kann. Hierfür wären als Empfänger 21 seismische Sensoren und eine entsprechende Ausgestaltung der Auswerteeinheit 22 vorteilhaft, wie sie in der GB-PS 1515447 oder der DE-OS 32 04 874 beschrieben sind. Der Komparator 38 wird in diesem Fall ein Ausgangssignal dann abgeben, wenn die gemessene Entfernung eine vorgegebene Minimalentfernung unterschreitet. Damit wird dann das Zündzeitwerk 19 aktiviert und der Treibladungszünder l4 getriggert. Die Sprengkapsel 12 wird mit der Anfangsgeschwindigkeit vo vertikal ausgestoßen und detoniert in vorgegebener Höhe nach Ablauf der konstanten Zündzeit.When using the mine against ground vehicles, the evaluation unit 22 is considerably simplified. Here the ignition timer 18 is always set to a constant ignition time, so that the ignition time calculator 29 and also the flight altitude calculator 33 are omitted. Receiver 21 and evaluation unit 22 must, however, be designed so that the distance of the ground vehicle from the mine can be determined. For this purpose, seismic sensors and a corresponding configuration of the evaluation unit 22 as described in GB-PS 1515447 or DE-OS 32 04 874 would be advantageous as receivers 21. In this case, the comparator 38 will emit an output signal if the measured distance falls below a predetermined minimum distance. The ignition timer 19 is then activated and the propellant charge igniter 14 is triggered. The detonator 12 is ejected vertically at the initial speed v o and detonates at a predetermined level after the constant ignition time has elapsed.

Claims (11)

1. Mine mit einem insbesondere verschießbaren Gehäuse, einer Sprengladung, einem Sprengladungszünder und einem Sensor zur Objektdetektion, dadurch gekennzeichnet, daß der Sprengladungszünder als Zeitzünder (17) mit Zündzeitwerk (18), Zündzeiteinsteller (19) und von dem Zündzeitwerk (18) betätigtem Zündauslöser (20) ausgebildet ist, daß die Sprengladung (16) und der Zeitzünder (17) in einer aus dem Gehäuse (10) ausstoßbaren Sprengkapsel (12) angeordnet sind, daß im Gehäuse (10) eine Treibladung (13) mit Treibladungszünder (14) zum im wesentlichen vertikalen Ausstoßen der Sprengkapsel (12) enthalten ist und daß der Sensor von einer Ortungsvorrichtung (42) mit mindestens einem Empfänger (21) und einer nachgeschalteten Auswerteeinheit (22) gebildet ist, die derart ausgebildet ist, daß sie aus den Empfangssignalen den Zündzeitpunkt für Treibladungszünder (14) und Zeitzünder (17) bestimmt und entsprechende Steuersignale ausgibt.1. Mine with a particularly lockable housing, an explosive charge, an explosive charge detonator and a sensor for object detection, characterized in that the explosive charge detonator as a time fuse (17) with ignition timer (18), ignition timing adjuster (19) and from the ignition timer (18) actuated trigger (20) is designed such that the explosive charge (16) and the time fuse (17) are arranged in an explosive capsule (12) which can be ejected from the housing (10), that in the housing (10) a propellant charge (13) with a propellant charge igniter (14) for substantially vertical ejection of the detonator capsule (12) and that the sensor is formed by a locating device (42) with at least one receiver (21) and a downstream evaluation unit (22), which is designed in such a way that it detects the received signals Ignition timing for propellant charge igniter (14) and time igniter (17) determined and outputs corresponding control signals. 2. Mine nach Anspruch 1, dadurch gekennzeichnet, daß ein Steuersignal als Einstellzeitsignal an dem Zündzeiteinsteller (19) und ein Steuersignal sowohl als Zündsignal an dem Treibladungszünder (14) als auch als Aktivierungssignal an dem Zündzeitwerk (18) liegt.2. Mine according to claim 1, characterized in that a control signal as a response time signal to the ignition timing adjuster (19) and a control signal is present both as an ignition signal at the propellant charge igniter (14) and as an activation signal at the ignition timer (18). 3. Mine nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Ortungsvorrichtung (42) mindestens einen akustischen Empfänger (21), wie Mikrophon oder Mikrophonanordnung, aufweist, der vorzugsweise im Gehäuse (10) integriert ist.3. Mine according to claim 1 or 2, characterized in that the locating device (42) at least one acoustic receiver (21), such as a microphone or microphone arrangement, which is preferably integrated in the housing (10). 4. Mine nach Anspruch 3, dadurch gekennzeichnet, daß der Empfänger (21) zwei rechtwinklig angeordnete Dipole aus vier jeweils an den Eckpunkten eines horizontal ausgerichteten Quadrats liegende elektro-akustische Wandler (23 bis 26) aufweist.4. Mine according to claim 3, characterized in that the receiver (21) has two dipoles arranged at right angles from four electro-acoustic transducers (23 to 26) each lying at the corner points of a horizontally oriented square. 5. Mine nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, daß die Auswerteeinheit (22) eine Schätzvorrichtung (28) zur zumindest annähernden Bestimmung der Flughöhe (hZ) eines Flugobjektes und einen Zündzeitrechner (29) aufweist, der aus der geschätzten Flughöhe (hZ) und der Ausstoßgeschwindigkeit (vo) der Sprengkapsel (12) deren Steigzeit (tZ) errechnet und daraus das Einstellzeitsignal für den Zündzeiteinsteller (19) ableitet.5. Mine according to one of claims 2 to 4, characterized in that the evaluation unit (22) has an estimation device (28) for at least approximately determining the flight altitude (h Z ) of a flying object and an ignition time calculator (29), which from the estimated flight altitude (h Z ) and the ejection speed (v o ) of the detonator capsule (12) calculates the rise time (t Z ) and derives the response time signal for the ignition timing adjuster (19). 6. Mine nach Anspruch 5, dadurch gekennzeichnet, daß die Schätzvorrichtung (28) eine Schaltungsanordnung (32) zur Bestimmung des Elevationswinkels (α) zum Flugobjekt und mindestens einer charakteristischen Frequenz (f) des Flugobjekts und einen Flughöhenrechner (33) aufweist, dem Elevationswinkel (≃) und Frequenz (f) einmal unmittelbar und einmal nach zeitlicher Differenzierung in jeweils einem Differenzierglied (34, 25) zugeführt sind.6. Mine according to claim 5, characterized in that the estimation device (28) has a circuit arrangement (32) for determining the elevation angle (α) to the flying object and at least one characteristic frequency (f) of the flying object and a flight altitude computer (33), the elevation angle (≃) and frequency (f) once immediately and once after time differentiation in a differentiator (34, 25) are supplied. 7. Mine nach Anspruch 5 oder 6, dadurch gekennzeichnet, daß ein Komparator (38) vorgesehen ist, der ein Ausgangssignal abgibt, wenn der Abstand (A) der Vertikalprojektion des Flugobjekts auf die Empfängerebene zu dem Empfänger (21) gleich oder kleiner als ein vorgegebener Maximalabstand (A max ) ist, und daß aus dem Ausgangssignal des Komparators (38) das Zündsignal für den Treibladungszünder (14) und das Aktivierungssignal für das Zündzeitwerk (18) abgeleitet sind.7. Mine according to claim 5 or 6, characterized in that a comparator (38) is provided which emits an output signal when the distance (A) of the vertical projection of the flying object on the receiver level to the receiver (21) is equal to or is smaller than a predetermined maximum distance (A max ), and that the ignition signal for the propellant charge igniter (14) and the activation signal for the ignition timer (18) are derived from the output signal of the comparator (38). 8. Mine nach Anspruch 7, dadurch gekennzeichnet, daß dem Komparator (38) ein Torglied (30) nachgeordnet ist, dessen Steuereingang mit einem weiteren, an dem Flughöhenrechner (33) angeschlossenen Komparator (31) derart verbunden ist, daß das Torglied (30) geöffnet ist, wenn die geschätzte Flughöhe (hZ) des Flugobjekts kleiner ist als eine maximale Steighöhe (h max ) der Sprengkapsel (12).8. Mine according to claim 7, characterized in that the comparator (38) is followed by a gate element (30), the control input of which is connected to a further comparator (31) connected to the flight altitude computer (33) such that the gate element (30 ) is open when the estimated flying height (h Z ) of the flying object is less than a maximum climbing height (h max) of the detonator (12). 9. Mine nach Anspruch 8, dadurch gekennzeichnet, daß eine Flugobjekt-Klassifizierungsvorrichtung (40) vorgesehen ist, die ein Signal an das Torglied (30) gibt, wenn ein aus den Empfangssignalen gewonnenes Frequenzspektrum mit einem vorgegebenen zumindest annähernd korreliert.9. Mine according to claim 8, characterized in that a flying object classification device (40) is provided which gives a signal to the gate member (30) when a frequency spectrum obtained from the received signals correlates at least approximately with a predetermined. 10. Mine nach Anspruch 8 und 9, dadurch gekennzeichnet, daß das Steuersignal am Steuereingang des Torgliedes (30) aus einer UND-Verknüpfung des Ausgangssignale des weiteren Komparators (31) und der Klassifizierungsvorrichtung (40) gebildet ist.10. Mine according to claim 8 and 9, characterized in that the control signal at the control input of the gate member (30) from an AND operation of the output signals of the further comparator (31) and the classification device (40) is formed. 11. Mine nach einem der Ansprüche 1 bis 10, dadurch gekennzeichnet, daß mit dem Gehäuse (10) ein Fallschirm (27) verbunden ist.11. Mine according to one of claims 1 to 10, characterized in that a parachute (27) is connected to the housing (10).
EP84108581A 1983-07-25 1984-07-20 Mine Expired - Lifetime EP0152516B1 (en)

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Cited By (3)

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GB2228066A (en) * 1985-12-11 1990-08-15 Dynamit Nobel Ag Mine for protection from moving objects.
EP0418566A1 (en) * 1989-08-22 1991-03-27 SenSys AG Detection device for the typical signals of a helicopter and for firing ground-air mines
FR2694389A1 (en) * 1992-07-30 1994-02-04 Saint Louis Inst Defense device.

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DE3515497A1 (en) * 1985-04-30 1986-10-30 Diehl GmbH & Co, 8500 Nürnberg ARMOR DEVICE MINE
DE3515496A1 (en) * 1985-04-30 1992-03-26 Diehl Gmbh & Co HELICOPTER DEVICE HIGH CHARGE MINE
IL86525A0 (en) * 1988-05-27 1988-11-15 Cohen David Promixity detector mine system
DE4034618C2 (en) * 1990-10-31 1997-03-27 Diehl Gmbh & Co mine

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DE3017797A1 (en) * 1980-05-09 1981-11-12 Fried. Krupp Gmbh, 4300 Essen METHOD FOR DETERMINING THE DIRECTIONS
DE3101722A1 (en) * 1981-01-21 1982-08-12 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Device for weapon release
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2228066A (en) * 1985-12-11 1990-08-15 Dynamit Nobel Ag Mine for protection from moving objects.
GB2228066B (en) * 1985-12-11 1991-01-02 Dynamit Nobel Ag Mine for repelling objects moving through adjacent air space at low altitude.
EP0418566A1 (en) * 1989-08-22 1991-03-27 SenSys AG Detection device for the typical signals of a helicopter and for firing ground-air mines
FR2694389A1 (en) * 1992-07-30 1994-02-04 Saint Louis Inst Defense device.

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DE3326748A1 (en) 1985-02-07
ATE54747T1 (en) 1990-08-15
EP0152516A3 (en) 1988-05-11
DE3326748C2 (en) 1990-12-06
EP0152516B1 (en) 1990-07-18

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