EP0152516B1 - Mine - Google Patents

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Publication number
EP0152516B1
EP0152516B1 EP84108581A EP84108581A EP0152516B1 EP 0152516 B1 EP0152516 B1 EP 0152516B1 EP 84108581 A EP84108581 A EP 84108581A EP 84108581 A EP84108581 A EP 84108581A EP 0152516 B1 EP0152516 B1 EP 0152516B1
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EP
European Patent Office
Prior art keywords
ignition
signal
mine according
mine
ignition point
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.)
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EP84108581A
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German (de)
French (fr)
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EP0152516A2 (en
EP0152516A3 (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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Publication of EP0152516A3 publication Critical patent/EP0152516A3/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 the 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 combat vehicles or mining vehicles.
  • a land mine of the type mentioned at the beginning is known as a so-called jumping mine ("the S-Mine 35", Why-Revue 14, 1974, pages 2277 to 2286).
  • this spring mine has three pressure pins, which are actuated at a pressure of 3 to 3.5 kg and release a spring-loaded firing pin, which forms the propellant detonator together with a primer.
  • the propellant charge When the propellant charge is ignited, it throws the detonator with the explosive charge and detonator out of the housing embedded in the ground and simultaneously ignites three delay tubes inside the detonator, which form the ignition mechanism of the propellant detonator with a fixed ignition time.
  • the ignition time of the delay tube is set such that the explosive charge is ignited while the detonator is jumping when the detonator has jumped out of the ground by about 0.7 to 1.5 m.
  • a device for triggering weapons by rolling, taking off or flying over aircraft is known.
  • Such weapons especially used at airports, such as So-called mines are triggered due to the ground and airborne noise generated by aircraft.
  • the device has a sound pickup, the received signal of which is examined for a signature that is significant due to a taxiing or overflowing aircraft. If there is one, the weapon is triggered.
  • the invention has for its object to provide mines of the type mentioned, which also reliably secure the air space above their 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. As soon as the helicopter penetrates into the area of action of the mine, a detonation body is ejected vertically and detonated approximately at the flying height of the helicopter. 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, e.g. 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. In this way, e.g. destroy the optical equipment of a modern main 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, by detaching the housing cover 11.
  • 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 a detonator timer 18, an ignition time adjuster 19 and an ignition trigger 20 actuated by the ignition timer 18.
  • 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 such 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, generates an ignition signal for the propellant charge igniter 14 and an activation signal for the ignition timer 18.
  • 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 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 computer 29 calculates the rise time t z from the estimated flight altitude h z and the ejection speed v o of the detonator capsule 12 and derives therefrom a response time signal which is at the input of the ignition timing adjuster 19 connected to the ignition timing 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 a to the flying object and for determining at least one characteristic frequency f of the flying object.
  • a circuit arrangement which can also determine the azimuth angle 1j '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 the elevation angle ⁇ and on the other hand a selected frequency f from the frequency spectrum of the measured flying object are supplied both in a differentiating element 34 and 35, both immediately and after time differentiation.
  • the flight altitude calculator 33 uses this to calculate the flight altitude h z of the measured target
  • the output of the circuit arrangement 32 leading to the elevation angle a for frequency and elevation angle determination is connected to a computing element 36 which measures the tangent of the Elevation angle value a is calculated.
  • the output of the arithmetic element 36 is connected to a multiplier 37, which has its other input on the Output of the flight altitude calculator 33 is connected.
  • the specified 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 maximum 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, via a connecting line 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 frequency and elevation angle determination, 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 agrees with 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, i.e. the measured flying object has been classified as a target to be combated and, of course, when its flight altitude h z is less than the maximum height hmax of the detonator 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 timer 29 and the flight altitude calculator 33 are omitted.
  • Receiver 21 and evaluation unit 22 must, however, be designed such 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)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Portable Nailing Machines And Staplers (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 dgl., 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 the 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 Kampffahrzeuge oder Minenrämfahrzeuge, 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 combat vehicles or mining vehicles.

Eine Landmine der eingangs genannten Art ist als sog. Springmine bekannt ("die S-Mine 35", Waffen-Revue 14, 1974, Seite 2277 bis 2286). Diese Springmine weist als Sensor zur Objektdetektion drei Druckstifte auf, die bei einem Druck von 3 bis 3,5 kg betätigt werden und einen federgespannten Schlagbolzen freigeben, der zusammen mit einem Zündhütchen den Treibladungszünder bildet. Mit Zünden der Treibladung schleudert diese die Sprengkapsel mit Sprengladung und Sprengladungszünder aus dem im Erdboden eingelassenen Gehäuse heraus und zündet gleichzeitig im Innern der Sprengkapsel drei Verzögerungsröhrchen, die das Zündzeitwerk des Treibladungszünders mit fest eingestellter Zündzeit bilden. Die Zündzeit dert Verzögerungsröchrchen ist so eingestellt, daß während des Springens der Sprengkapsel die Sprengladung dann gezündet wird, wenn die Sprengkapsel etwa 0,7 bis 1,5 m aus dem Erdboden herausgesprungen ist.A land mine of the type mentioned at the beginning is known as a so-called jumping mine ("the S-Mine 35", Waffen-Revue 14, 1974, pages 2277 to 2286). As a sensor for object detection, this spring mine has three pressure pins, which are actuated at a pressure of 3 to 3.5 kg and release a spring-loaded firing pin, which forms the propellant detonator together with a primer. When the propellant charge is ignited, it throws the detonator with the explosive charge and detonator out of the housing embedded in the ground and simultaneously ignites three delay tubes inside the detonator, which form the ignition mechanism of the propellant detonator with a fixed ignition time. The ignition time of the delay tube is set such that the explosive charge is ignited while the detonator is jumping when the detonator has jumped out of the ground by about 0.7 to 1.5 m.

Eine solche Landmine wirkt ausschließlich gegen lebende Ziele im Umkreis von ca. 20 m und muß durch mechanischen Druck ausgelöst werden. Als Abwehrmittel gegen tieffliegende Hubschrauber ist sie schon aus Gründen des Druckzünders unbrauchbar.Such a land mine only works against living targets within a radius of approx. 20 m and must be triggered by mechanical pressure. As a defense against low-flying helicopters, it is unusable for reasons of the pressure igniter.

Aus der DE 31 01 722 A1 ist eine Vorrichtung für die Waffenauslösung durch rollende, startende oder überfliegende Flugzeuge bekannt. Solche, insbesondere auf Flughäfen eingesetzte Waffen, wie z.B. sog. Lauerminen, werden aufgrund des von Flugzeugen erzeugten Boden- und Luftschalls ausgelöst. Hierzu weist die Vorrichtung einen Schallaufnehmer auf, dessen Empfangssignal auf eine durch ein rollendes bzw. überfliegendes Flugzeug signifikante Signatur untersucht wird. Liegt eine solche vor, so erfolgt die Auslösung der Waffe.From DE 31 01 722 A1 a device for triggering weapons by rolling, taking off or flying over aircraft is known. Such weapons, especially used at airports, such as So-called mines are triggered due to the ground and airborne noise generated by aircraft. For this purpose, the device has a sound pickup, the received signal of which is examined for a signature that is significant due to a taxiing or overflowing aircraft. If there is one, the weapon is triggered.

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 reliably secure the air space above their 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 Husbschrauber 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 according to the invention in a mine of the type specified in the preamble of claim 1 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 previously used for this purpose, such as missile-guided missiles, helicopter defense helicopters, or conventional tubular 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 barrel weapons, on the other hand, are generally not very effective, since husbikes approach the target area low-flying using the cover options provided by the terrain, so that on the one hand they do not offer a sufficiently good target for the barrel weapon and, on the other hand, they cannot be located early, what a successful use of the barrel 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 Hubscrauber 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. As soon as the helicopter penetrates into the area of action of the mine, a detonation body is ejected vertically and detonated approximately at the flying height of the helicopter. 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, e.g. 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, e.g. destroy the optical equipment of a modern main 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 Zünderzeitwerk 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, by detaching the housing cover 11. 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 a detonator timer 18, an ignition time adjuster 19 and an ignition trigger 20 actuated by the 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. 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 such 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, generates an ignition signal for the propellant charge igniter 14 and an activation signal for the ignition timer 18.

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 Quardrats 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 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 einem 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 der Ausstoßgeschwindigkeit vo der Sprengkapsel 12 deren Steigzeit tz gemäß

Figure imgb0001
und leitet daraus ein Einstellzeitsignal ab, das an dem Eingang des mit dem Zündzeitrechner 29 verbundenen Zündzeiteinstellers 19 liegt. Entsprechend diesem Einstellzeitsignal wird die Zündzeit des Zündzeitwerks 18 eingestellt.As 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 computer 29 calculates the rise time t z from the estimated flight altitude h z and the ejection speed v o of the detonator capsule 12
Figure imgb0001
 and derives therefrom a response time signal which is at the input of the ignition timing adjuster 19 connected to the ignition timing 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 a zum Flugobjekt und zur Bestimmung mindestens einer charakteristischen Frequenz f des Flugobjekts auf. Eine solche Schaltungsanordnung, die zudem noch den Azimutwinkel 1j' zum Flugobjekt betimmen 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 a und 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 imgb0002
The flight altitude estimation device 28 has a circuit arrangement 32 for determining the elevation angle a to the flying object and for determining at least one characteristic frequency f of the flying object. Such a circuit arrangement, which can also determine the azimuth angle 1j '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 the elevation angle α and on the other hand a selected frequency f from the frequency spectrum of the measured flying object are supplied both in a differentiating element 34 and 35, both immediately and after time differentiation. The flight altitude calculator 33 uses this to calculate the flight altitude h z of the measured target
Figure imgb0002

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 a führende Ausgang der Schaltungsandordnung 32 zur Frequenz- und Elevationswinkelbestimmung mit einem Rechenglied 36 verbunden, das den Tangens des Elevationswinkelwertes a 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-tana 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 vorgegbene 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 Amax, 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 at ignition time, the output of the circuit arrangement 32 leading to the elevation angle a for frequency and elevation angle determination is connected to a computing element 36 which measures the tangent of the Elevation angle value a is calculated. The output of the arithmetic element 36 is connected to a multiplier 37, which has its other input on the Output of the flight altitude calculator 33 is connected. The multiplier 37 calculates the distance A = h z -tana of 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 specified 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 maximum 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, via a connecting line 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 hmax 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 frequency and elevation angle determination, 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 agrees with 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, i.e. the measured flying object has been classified as a target to be combated and, of course, when its flight altitude h z is less than the maximum height hmax of the detonator 12.

Bei Einsatz der Mine gegen Bodenfahrzeuge vereinfacht sich die Auswerteeinheit 22 erheblich. Hier wird das Zündzeitwerk 18 immer auf eine konstante Zündzeit eingestellt, so daß 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 14 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 timer 29 and the flight altitude calculator 33 are omitted. Receiver 21 and evaluation unit 22 must, however, be designed such 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 (12)

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) acutated 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.
2. A mine according to claim 1, characterized in that out of the control signals delivered by the evaluating unit (22) a control signal is applied as an adjusting time signal to-the ignition point adjuster (19) of the explosive charge ignition device (17), and a control signal is applied both as an ignition signal to the propellant charge ignition device (14) and also as an activation signal to the ignition point mechanism (18).
3. A mine according to claims 1 or 2, characterized in that the locating device (42) has at least one acoustic receiver (21), such as a microphone or microphone arrangement, which is preferably integrated in the casing (10).
4. A mine according to claim 3, characterized in that the receiver (21) has two dipoles disposed at right angles and comprising four electro-acoustic transducers (23 to 26) each disposed at the corner points of a horizontally aligned square.
5. A mine according to one of claims 2 to 4, characterized in that the evaluating unit (22) has an estimating device (28) to at least approximately determine the flight altitude (hz) of a flying object and an ignition point computer (29) which computes the time of climb (tz) of the detonation cap (12) from the estimated flight altitude (hz) and the ejection speed (vo) of the detonating cap (12) and derives therefrom the adjusting time signal for the ignition point adjuster (19).
6. A mine according to claim 5, characterised in that the estimating device (28) has a circuit arrangement (32) for determining the angle of elevation (a) to the flying object and at least one characteristic frequency (f) thereof and a flight altitude computer (33) to which the angle of elevation (a) and the frequency (f) are supplied on the one hand directly and on the other hand after time differentiation in a differentiating component (34, 25) respectively.
7. A mine according to claims 5 or 6, characterized in that a comparator (38) is provided which delivers an output signal when the distance (A) between the vertical projection of the flying object to the receiver plane and the receiver (21) is equal to or smaller than a given maximum distance (Amax). and the ignition signal for the propellant charge ignition device (14) and the activation signal for the ignition point mechanism (18) are derived from the output signal of the comparator (38).
8. A mine according to claim 7, characterized in that the comparator (38) is followed by a gate member (30) whose control input is so connected to a further comparator (31) connected to the flight altitude computer (33) that the gate member (30) is opened when the estimated flight altitude (hz) of the flying object is smaller than a maximum height of climb (hmax) of the detonation cap (12).
9. A mine according to claim 8, characterized in that a flying object classifying device (40) is provided which delivers a signal to the gate member (30) when a frequency spectrum obtained from the received signals correlates at least approximately with a given frequency spectrum.
10. A mine according to claims 8 and 9, characterized in that the control signal is formed at the control input of the gate member (30) from an AND connection of the output signal of the further comparator (31) and of the classifying device (40).
11, A mine according to one of claims 1 to 10, characterized in that the casing (10) can be shot.
12. A mine according to claim 11, characterized in that a parachute (27) is connected to the casing (10).
EP84108581A 1983-07-25 1984-07-20 Mine Expired - Lifetime EP0152516B1 (en)

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DE19833326748 DE3326748A1 (en) 1983-07-25 1983-07-25 MINE
DE3326748 1983-07-25

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EP0152516A3 EP0152516A3 (en) 1988-05-11
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DE3515496A1 (en) * 1985-04-30 1992-03-26 Diehl Gmbh & Co HELICOPTER DEVICE HIGH CHARGE MINE
DE3515497A1 (en) * 1985-04-30 1986-10-30 Diehl GmbH & Co, 8500 Nürnberg ARMOR DEVICE MINE
DE3543769A1 (en) * 1985-12-11 1990-05-31 Dynamit Nobel Ag Mine for defence against moving objects
IL86525A0 (en) * 1988-05-27 1988-11-15 Cohen David Promixity detector mine system
DE3927663C3 (en) * 1989-08-22 1998-11-12 Hirtenberger Ag Device for target detection and launching of ground-to-air mines to be fired in helicopter combat
DE4034618C2 (en) * 1990-10-31 1997-03-27 Diehl Gmbh & Co mine
DE4225233A1 (en) * 1992-07-30 1994-02-03 Deutsch Franz Forsch Inst Automatic defence system using missile launcher - has primary and secondary electromagnetic windings on missile and launcher automatically triggered by enemy sensor

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DE2509705C3 (en) * 1975-03-06 1981-07-23 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Mine, especially land mine
US4001771A (en) * 1975-10-20 1977-01-04 International Business Machines Corporation Intruder detecting security system
AT346734B (en) * 1976-02-03 1978-11-27 Oregon Ets Patentverwertung SPRINGMINE
DE3017797A1 (en) * 1980-05-09 1981-11-12 Fried. Krupp Gmbh, 4300 Essen METHOD FOR DETERMINING THE DIRECTIONS
DE3101722C2 (en) * 1981-01-21 1983-10-06 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Device for triggering weapons
DE3204874C2 (en) * 1982-02-11 1994-07-14 Atlas Elektronik Gmbh Passive method for obtaining target data from a sound source
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DE3326748C2 (en) 1990-12-06
EP0152516A2 (en) 1985-08-28
ATE54747T1 (en) 1990-08-15
DE3326748A1 (en) 1985-02-07
EP0152516A3 (en) 1988-05-11

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