EP1394495A1 - Apparatus for fighting against targets - Google Patents

Apparatus for fighting against targets Download PDF

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Publication number
EP1394495A1
EP1394495A1 EP03014218A EP03014218A EP1394495A1 EP 1394495 A1 EP1394495 A1 EP 1394495A1 EP 03014218 A EP03014218 A EP 03014218A EP 03014218 A EP03014218 A EP 03014218A EP 1394495 A1 EP1394495 A1 EP 1394495A1
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EP
European Patent Office
Prior art keywords
sensor
missile
target
seeker
evaluation device
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP03014218A
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German (de)
French (fr)
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EP1394495B1 (en
Inventor
Ralf-Joachim Dr. Herrmann
Wolfgang Dr. Seidel
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Rheinmetall Waffe Munition GmbH
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Rheinmetall W&M GmbH
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Publication of EP1394495A1 publication Critical patent/EP1394495A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G5/00—Elevating or traversing control systems for guns
    • F41G5/12—Elevating or traversing control systems for guns acoustically influenced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G5/00—Elevating or traversing control systems for guns
    • F41G5/08—Ground-based tracking-systems for aerial targets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves

Definitions

  • the invention relates to a device for combating targets within a area to be monitored with an earthbound directional launcher, a target detection device connected to the launcher and at least one that can be fired from the launcher Missiles.
  • DE 31 40 728 C2 for example, is known for combating Panzer an accurate determination of the destination by a combination of passive and active sensors.
  • the passive serve Sensors e.g. acoustic sensors
  • the active sensors for determining the target speed. From the Changing the target direction and the speed of the drag can then change the trajectory of the target and thus also the firing time of the missile be determined.
  • a disadvantage of these known devices is, inter alia, that for Path determination of the target and the subsequent aiming of the launcher the missile takes a relatively long time, so that the response time of the Device from receiving the acoustic target characteristic signals to Firing the missile to combat very fast targets, such as Helicopters, is too long.
  • active Sensors of the targeting device the risk that the opponent's ground-based Can locate and destroy launcher.
  • the invention has for its object a device of the beginning Specify mentioned type, which is simple and inexpensive, a short Has response time and their launch and target detection facility through the use of appropriate sensors cannot be located.
  • the invention is essentially based on the idea that the device a target detection device that includes only passive sensors used and only the direction of the target, but not the trajectory of the target to be combated before the assigned missile is shot down determined, and that the missile of the device has a seeker head for Firing the missile in the target direction (e.g. using an infrared sensor) autonomously searches for the target and then destroys it.
  • a locatable connection between the Missile and the launcher or the targeting device does not exist during the flight phase of the missile.
  • the device according to the invention has the advantage that it is relatively small autonomous unit e.g. manually within an area to be monitored can be installed and monitors the corresponding room area for a long time.
  • the device is equipped with e.g. provided acoustic alarm sensor.
  • the Target acquisition device then carries out a permanent frequency analysis of the received acoustic signals.
  • the bearing sensor is activated and the Bearing angle to the target determined.
  • the launcher is in the direction of the bearing aligned and the missile (e.g. a "Stinger" rocket) shot down.
  • the missile's infrared sensor looks for a heat source (target) in the through the acoustic bearing specific space segment, and the missile is by means of a appropriate steering device led to the target.
  • the acoustic DF sensor at least four microphones, each at the corner points of one Tetrahedra are arranged.
  • the wake-up sensor is preferably one of the microphones of the Peilsensors.
  • 1 is a device for combating according to the invention of helicopters 2 within a specified area to be monitored designated.
  • the device 1 consists of a housing 3 in which both a Power supply unit and an electronic evaluation device 4 a target detection device 5 is accommodated (see also FIG. 3).
  • a straightening system 6 adjoins the housing 3 at the top, by means of which a launcher 7 can be aimed in azimuth and elevation.
  • three legs 8 are arranged laterally, which on the Support ground 9 and where three microphones 10 of an acoustic DF sensor 11 are attached.
  • a fourth microphone 10 of the acoustic DF sensor 11 is arranged on the straightening system 6, so that the four microphones 10 of the DF sensor 11 form the corner points of a tetrahedron. All microphones 10 of the DF sensors 11 are connected to the electronic via electrical lines 12 Evaluation device 4 connected. This contains a microprocessor 13.
  • At least one missile 14 is arranged in the launcher 7, which with a target-searching IR search head 15 and one not shown Steering device is provided.
  • the device 1 After the device 1 has been set up, it is switched on. After that is located The device 1 is initially in a so-called listening mode, i.e. it is only one acoustic alarm circuit which is connected to only one of the microphones 10, activated.
  • the electronic evaluation device 4 permanently performs a fast Fourier transformation (FFT) of that measured by the microphone 10 in each case through acoustic signals. Once the frequency spectrum of the acoustic Similar to the signature of a helicopter, the targeting device in the so-called DF mode.
  • FFT fast Fourier transformation
  • the electronic ones Evaluation device 4 determines the spatial direction to the target 2.
  • the acoustic signals coming from the target 2 are emitted by the microphones 10 measured with a time delay. This phase shift then becomes of the microprocessor 13 determines the spatial direction of the target 2.
  • the launcher 7 is in azimuth and Elevation directed by the straightening system 6 such that the missile 14 in Direction of the acoustic bearing shows.
  • the IR sensor of the Search head 15 of the missile 14 cooled to operating temperature and one Friend-foe identifier queried and in case of enemy missile 14 shot down.
  • the missile 14 is accelerated to supersonic speed and the IR seeker head 15 searches for a target (heat source) in the room segment that is created by the acoustic bearing was determined. After target 2 is captured, the Missile 14 is guided to the target by means of an IR seeker head 15 and a steering device.
  • the invention is of course not limited to that described above Embodiment limited.
  • the search head of the Missile also act as a radar seeker.
  • the missile is not fired until the seeker head even before the missile was launched the target in the acoustic bearing defined space segment.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Acoustics & Sound (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Catching Or Destruction (AREA)
  • Soil Working Implements (AREA)
  • Plasma Technology (AREA)
  • Measurement Of Velocity Or Position Using Acoustic Or Ultrasonic Waves (AREA)

Abstract

The missile launcher (1) has a tube (7) mounted on trunnions on a rotatable column (6) so that it may be aimed in the general direction of a target, e.g. an enemy helicopter (2), as determined by acoustic sensing. The guided missile (14) with an infrared target-seeking head (15) is loaded into the tube ready for use. The rotatable column supporting the tube may be mounted on a housing (3) which contains the microprocessor and other electronic equipment. There are stabilizing legs (8) resting on the ground (9) and carrying microphones (10) and level sensors (11). The noise made by the helicopter is recognized and its level is assessed, and the missile may be launched when the noise gets sufficiently loud.

Description

Die Erfindung betrifft eine Vorrichtung zur Bekämpfung von Zielen innerhalb eines zu überwachenden Bereiches mit einer erdgebundenen richtbaren Abschußeinrichtung, einer mit der Abschußeinrichtung verbundenen Zielertassungseinrichtung und mindestens einem aus der Abschußeinrichtung verschießbaren Flugkörper.The invention relates to a device for combating targets within a area to be monitored with an earthbound directional launcher, a target detection device connected to the launcher and at least one that can be fired from the launcher Missiles.

Aus der DE 31 40 728 C2 ist beispielsweise bekannt, zur Bekämpfung von Panzern eine genaue Ermittlung des Zielortes durch eine Kombination von passiven und aktiven Sensoren vorzunehmen. Dabei dienen die passiven Sensoren (z.B. akustische Sensoren) zur Ermittlung der jeweiligen Zielrichtung und die aktiven Sensoren zur Bestimmung der Zielgeschwindigkeit. Aus der Änderung der Zielrichtung und der Zieigeschwindigkeit kann dann die Bewegungsbahn des Zieles und damit auch der Abfeuerzeitpunkt des Flugkörpers ermittelt werden.DE 31 40 728 C2, for example, is known for combating Panzer an accurate determination of the destination by a combination of passive and active sensors. The passive serve Sensors (e.g. acoustic sensors) to determine the respective target direction and the active sensors for determining the target speed. From the Changing the target direction and the speed of the drag can then change the trajectory of the target and thus also the firing time of the missile be determined.

Nachteilig ist bei diesen bekannten Vorrichtungen unter anderem, daß für die Bahnermittlung des Zieles und das anschließende Richten der Abschußeinrichtung des Flugkörpers relativ viel Zeit benötigt wird, so daß die Reaktionszeit der Vorrichtung vom Empfang der akustischen zielcharakteristischenSignale bis zum Abfeuern des Flugkörpers für die Bekämpfung sehr schneller Ziele, etwa von Hubschraubern, zu lang ist. Außerdem besteht durch die Verwendung der aktiven Sensoren der Zielerfassungseinrichtung die Gefahr, daß der Gegner die bodengebundene Abschußeinrichtung orten und zerstören kann. A disadvantage of these known devices is, inter alia, that for Path determination of the target and the subsequent aiming of the launcher the missile takes a relatively long time, so that the response time of the Device from receiving the acoustic target characteristic signals to Firing the missile to combat very fast targets, such as Helicopters, is too long. There is also the use of active Sensors of the targeting device the risk that the opponent's ground-based Can locate and destroy launcher.

Der Erfindung liegt die Aufgabe zugrunde, eine Vorrichtung der eingangs erwähnten Art anzugeben, die einfach und kostengünstig aufgebaut ist, eine kurze Reaktionszeit besitzt und deren Abschuß- und Zielerfassungseinrichtung durch die Verwendung entsprechender Sensoren nicht ortbar ist.The invention has for its object a device of the beginning Specify mentioned type, which is simple and inexpensive, a short Has response time and their launch and target detection facility through the use of appropriate sensors cannot be located.

Diese Aufgabe wird erfindungsgemäß durch die Merkmale des Anspruchs 1 gelöst. Weitere, besonders vorteilhafte Ausgestaltungen der Erfindung offenbaren die Unteransprüche.This object is achieved by the features of claim 1 solved. Reveal further, particularly advantageous embodiments of the invention the subclaims.

Die Erfindung beruht im wesentlichen auf dem Gedanken, daß die Vorrichtung eine Zielerfassungseinrichtung umfaßt, die ausschließlich passive Sensoren verwendet und die lediglich die Zielrichtung, nicht aber die Bewegungsbahn des zu bekämpfenden Zieles vor dem Abschuß des zugeordneten Flugkörpers ermittelt, und daß der Flugkörper der Vorrichtung einen Suchkopf besitzt, der nach Abschuß des Flugkörpers in Zielrichtung (z.B. mittels eines Infrarot-Sensors) autonom das Ziel sucht und dann zerstört. Eine ortbare Verbindung zwischen dem Flugkörper und der Abschußvorrichtung bzw. der Zielerfassungseinrichtung besteht während der Flugphase des Flugkörpers nicht.The invention is essentially based on the idea that the device a target detection device that includes only passive sensors used and only the direction of the target, but not the trajectory of the target to be combated before the assigned missile is shot down determined, and that the missile of the device has a seeker head for Firing the missile in the target direction (e.g. using an infrared sensor) autonomously searches for the target and then destroys it. A locatable connection between the Missile and the launcher or the targeting device does not exist during the flight phase of the missile.

Die erfindungsgemäße Vorrichtung weist den Vorteil auf, daß sie als relativ kleine autonome Einheit z.B. manuell innerhalb eines zu überwachenden Gebietes installierbar ist und den entsprechenden Raumbereich für längere Zeit überwacht. Hierzu ist die Vorrichtung mit einem z.B. akustischen Wecksensor versehen. Die Zielerfassungseinrichtung führt dann eine permanente Frequenzanalyse der empfangenen akustischen Signale durch. Sobald das akustische Frequenzspektrum auf ein zu bekämpfendes Ziel hindeutet, wird der Peilsensor aktiviert und der Peilwinkel zum Ziel ermittelt. Die Abschußeinrichtung wird in Peilrichtung ausgerichtet und der Flugkörper (z.B. eine "Stinger"-Rakete) abgeschossen. Der Infrarot-Sensor der Rakete sucht dann eine Wärmequelle (Ziel) in dem durch die akustische Peilung bestimmten Raumsegment, und die Rakete wird mittels einer entsprechenden Lenkeinrichtung in das Ziel geführt.The device according to the invention has the advantage that it is relatively small autonomous unit e.g. manually within an area to be monitored can be installed and monitors the corresponding room area for a long time. For this purpose the device is equipped with e.g. provided acoustic alarm sensor. The Target acquisition device then carries out a permanent frequency analysis of the received acoustic signals. As soon as the acoustic frequency spectrum indicates a target to be fought, the bearing sensor is activated and the Bearing angle to the target determined. The launcher is in the direction of the bearing aligned and the missile (e.g. a "Stinger" rocket) shot down. The The missile's infrared sensor then looks for a heat source (target) in the through the acoustic bearing specific space segment, and the missile is by means of a appropriate steering device led to the target.

Bei einer vorteilhaften Ausführungsform der Erfindung umfaßt der akustische Peilsensor mindestens vier Mikrophone, welche jeweils an den Eckpunkten eines Tetraeders angeordnet sind.In an advantageous embodiment of the invention, the acoustic DF sensor at least four microphones, each at the corner points of one Tetrahedra are arranged.

Vorzugsweise handelt es sich bei dem Wecksensor um eines der Mikrophone des Peilsensors.The wake-up sensor is preferably one of the microphones of the Peilsensors.

Weitere Einzelheiten und Vorteile der Erfindung ergeben sich aus den folgenden anhand von Figuren erläuterten Ausführungsbeispielen. Es zeigen:

  • Fig.1 eine schematische Seitenansicht einer erfindungsgemäßen Vorrichtung zur Bekämpfung von Luftzielen;
  • Fig.2 eine Draufsicht auf die in Fig.1 dargestellte Vorrichtung und
  • Fig.3 ein Blockschaltbild einer Zielerfassungseinrichtung.
    • Further details and advantages of the invention result from the following exemplary embodiments explained with reference to figures. Show it:
  • 1 shows a schematic side view of a device according to the invention for combating air targets;
  • 2 shows a top view of the device shown in FIG
  • 3 shows a block diagram of a target detection device.

    • In den Fig.1 und 2 ist mit 1 eine erfindungsgemäße Vorrichtung zur Bekämpfung von Hubschraubern 2 innerhalb eines vorgebenen zu überwachenden Raumes bezeichnet. Die Vorrichtung 1 besteht aus einem Gehäuse 3, in dem sowohl eine Energieversorgungseinheit als auch eine elektronische Auswerteeinrichtung 4 einer Zielerfassungseinrichtung 5 untergebracht ist (vgl. auch Fig.3).1 and 2, 1 is a device for combating according to the invention of helicopters 2 within a specified area to be monitored designated. The device 1 consists of a housing 3 in which both a Power supply unit and an electronic evaluation device 4 a target detection device 5 is accommodated (see also FIG. 3).

    Oberseitig schließt sich an das Gehäuse 3 eine Richtanlage 6 an, mittels welcher eine Abschußeinrichtung 7 in Azimut und Elevation gerichtet werden kann.A straightening system 6 adjoins the housing 3 at the top, by means of which a launcher 7 can be aimed in azimuth and elevation.

    An dem Gehäuse 3 sind seitlich drei Beine 8 angeordnet, welche sich an dem Erdboden 9 abstützen und an denen drei Mikrophone 10 eines akustischen Peilsensors 11 befestigt sind. Ein viertes Mikrophon 10 des akustischen Peilsensors 11 ist an der Richtanlage 6 angeordnet, so daß die vier Mikrophone 10 des Peilsensors 11 die Eckpunkte eines Tetraeders bilden. Alle Mikrophone 10 des Peilsensors 11 sind über elektrische Leitungen 12 mit der elektronischen Auswerteeinrichtung 4 verbunden. Diese enthält einen Mikroprozessor 13. On the housing 3 three legs 8 are arranged laterally, which on the Support ground 9 and where three microphones 10 of an acoustic DF sensor 11 are attached. A fourth microphone 10 of the acoustic DF sensor 11 is arranged on the straightening system 6, so that the four microphones 10 of the DF sensor 11 form the corner points of a tetrahedron. All microphones 10 of the DF sensors 11 are connected to the electronic via electrical lines 12 Evaluation device 4 connected. This contains a microprocessor 13.

    In der Abschußeinrichtung 7 ist mindestens ein Flugkörper 14 angeordnet, welcher mit einem zielsuchenden IR-Suchkopf 15 und einer nicht dargestellten Lenkeinrichtung versehen ist.At least one missile 14 is arranged in the launcher 7, which with a target-searching IR search head 15 and one not shown Steering device is provided.

    Nachfolgend wird auf die Funktionsweise der erfindungsgemäßen Vorrichtung eingegangen.The mode of operation of the device according to the invention is described below received.

    Nach dem Aufstellen der Vorrichtung 1 wird diese eirgeschaitet. Danach befindet sich die Vorrichtung 1 zunächst in einem sog. Lauschmodus, d.h. es ist nur eine akustische Weckschaltung, die mit nur einem der Mikrophone 10 verbunden ist, aktiviert. Die elektronische Auswerteeinrichtung 4 führt permanent eine Fast Fourier Transformation (FFT) des jeweils von dem Mikrophon 10 gemessenen akustischen Signales durch. Sobald das Frequenzspektrum der akustischen Signatur eines Hubschraubers ähnelt, wird die Zielerfassungseinrichtung in den sog. Peilmodus versetzt.After the device 1 has been set up, it is switched on. After that is located The device 1 is initially in a so-called listening mode, i.e. it is only one acoustic alarm circuit which is connected to only one of the microphones 10, activated. The electronic evaluation device 4 permanently performs a fast Fourier transformation (FFT) of that measured by the microphone 10 in each case through acoustic signals. Once the frequency spectrum of the acoustic Similar to the signature of a helicopter, the targeting device in the so-called DF mode.

    Im Pellmodus sind alle vier Mikrophone 10 aktiviert und die elektronische Auswerteeinrichtung 4 bestimmt die räumliche Richtung zum Ziel 2. Hierzu werden die von dem Ziel 2 kommenden akustischen Signale von den Mikrophonen 10 zeitversetzt gemessen. Aus dieser Phasenverschiebung wird dann mittels des Mikroprozessors 13 die räumliche Richtung des Zieles 2 bestimmt.In the pell mode, all four microphones 10 are activated and the electronic ones Evaluation device 4 determines the spatial direction to the target 2. For this purpose the acoustic signals coming from the target 2 are emitted by the microphones 10 measured with a time delay. This phase shift then becomes of the microprocessor 13 determines the spatial direction of the target 2.

    Sobald die Peilung stabil und das Frequenzspektrum als die akustische Signatur eines Hubschraubers identifiziert ist, wird die Abschußeinrichtung 7 in Azimut und Elevation mittels der Richtanlage 6 derart gerichtet, daß der Flugkörper 14 in Richtung der akustischen Peilung zeigt. Gleichzeitig wird der IR-Sensor des Suchkopfes 15 des Flugkörpers 14 auf Betriebstemperatur gekühlt und eine Freund-Feind Kennung abgefragt und im Feindfall der Flugkörper 14 abgeschossen.Once the bearing is stable and the frequency spectrum as the acoustic signature a helicopter is identified, the launcher 7 is in azimuth and Elevation directed by the straightening system 6 such that the missile 14 in Direction of the acoustic bearing shows. At the same time, the IR sensor of the Search head 15 of the missile 14 cooled to operating temperature and one Friend-foe identifier queried and in case of enemy missile 14 shot down.

    Der Flugkörper 14 wird auf Überschallgeschwindigkeit beschleunigt und der IR-Suchkopf 15 sucht ein Ziel (Wärmequelle) in dem Raumsegment, das durch die akustische Peilung bestimmt wurde. Nach Erfassung des Zieles 2 wird der Flugkörper 14 mittels IR-Suchkopf 15 und Lenkeinrichtung ins Ziel geführt.The missile 14 is accelerated to supersonic speed and the IR seeker head 15 searches for a target (heat source) in the room segment that is created by the acoustic bearing was determined. After target 2 is captured, the Missile 14 is guided to the target by means of an IR seeker head 15 and a steering device.

    Die Erfindung ist selbstverständlich nicht auf das vorstehend beschriebene Ausführungsbeispiel beschränkt. So kann es sich bei dem Suchkopf des Flugkörpers auch um einen Radar-Suchkopf handeln.The invention is of course not limited to that described above Embodiment limited. The search head of the Missile also act as a radar seeker.

    Im Falle der Verwendung eines passiven IR-Suchkopfes kann außerdem vorgesehen sein, daß der Flugkörper erst abgeschossen wird, wenn der Suchkopf bereits vor Abschuß des Flugkörpers das Ziel in dem durch die akustische Peilung definierten Raumsegment detektiert hat. In the case of using a passive IR seeker head it can also be provided that the missile is not fired until the seeker head even before the missile was launched the target in the acoustic bearing defined space segment.

    BezugszeichenlisteLIST OF REFERENCE NUMBERS

    11
    Vorrichtungcontraption
    22
    Ziel, HubschrauberAim, helicopter
    33
    Gehäusecasing
    44
    (elektronische) Auswerteeinrichtung(electronic) evaluation device
    55
    ZielerfassungseinrichtungTarget detection device
    66
    Richtanlagestraightening plant
    77
    Abschußeinrichtunglauncher
    88th
    Beinleg
    99
    Erdbodenground
    1010
    Sensor, Mikrophon, WecksensorSensor, microphone, alarm sensor
    1111
    Peilsensorbearing sensor
    1212
    elektrische Leitungelectrical line
    1313
    Mikroprozessormicroprocessor
    1414
    Flugkörpermissile
    1515
    Suchkopfseeker

    Claims (6)

    Vorrichtung zur Bekämpfung von Zielen (2) innerhalb eines zu überwachenden Bereiches mit einer erdgebundenen richtbaren Abschußeinrichtung (7), einer mit der Abschußeinrichtung (7) verbundenen Zielerfassungseinrichtung (5) und mindestens einem aus der Abschußeinrichtung (7) verschießbaren Flugkörper (14), mit den Merkmalen: a) der Flugkörper (14) besitzt einen zielsuchenden Suchkopf (15); b) die Zielerfassungseinrichtung (5) umfaßt eine elektronische Auswerteeinrichtung (4), einen mit der Auswerteeinrichtung (4) verbundenen passiven, akustischen Wecksensor (10) und einen mit der Auswertevorrichtung (4) verbundenen passiven akustischen Peilsensor (11) zur Bestimmung der Zielrichtung; c) die einzelnen Baugruppen der Vorrichtung (1) stehen derart miteinander in Wirkverbindung, daß die elektronische Auswerteeinrichtung (4) nach dem Empfang zielcharakteristischer Signale mittels des Wecksensors (10) den Peilsensor (11) aktiviert, Signalwerte zur Ausrichtung der Abschußeinrichtung in Zielrichtung ermittelt und die entsprechenden Stellantriebe der Richtanlage (6) der Abschußeinrichtung (7) ansteuert, und daß dann der Flugkörper (14) in Zielrichtung abgeschossen wird und mit seinem Suchkopf (15) autonom die Zielfindung übernimmt. Device for combating targets (2) within an area to be monitored with an earthbound directional launch device (7), a target detection device (5) connected to the launch device (7) and at least one missile (14) that can be fired from the launch device (7) the characteristics: a) the missile (14) has a seeker seeker (15); b) the target detection device (5) comprises an electronic evaluation device (4), a passive acoustic alarm sensor (10) connected to the evaluation device (4) and a passive acoustic direction finder sensor (11) connected to the evaluation device (4) for determining the target direction; c) the individual assemblies of the device (1) are operatively connected to one another in such a way that the electronic evaluation device (4) activates the direction-finding sensor (11) after receiving target-specific signals by means of the wake-up sensor (10), determines signal values for aligning the launcher in the target direction and controls the corresponding actuators of the aiming system (6) of the launcher (7), and that the missile (14) is then fired in the target direction and autonomously takes over the aiming with its seeker head (15). Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß der akustische Peilsensor (11) mindestens vier Mikrophone (10) umfaßt, welche jeweils an den Eckpunkten eines Tetraeders angeordnet sind. Apparatus according to claim 1, characterized in that the acoustic bearing sensor (11) comprises at least four microphones (10), which are each arranged at the corner points of a tetrahedron. Vorrichtung nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß es sich bei dem Wecksensor (10) um eines der Mikrophone des Peilsensors (11) handelt.Device according to claim 1 or 2, characterized in that the wake-up sensor (10) is one of the microphones of the direction-finding sensor (11). Vorrichtung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die elektronische Auswerieeinrichtung (4) einen Mikroprozessor (13) zur Durchführung einer Fourier-Analyse der gemessenen Schallsignale des Wecksensors (10) vornimmt, und daß diese Signalwerte mit für das Ziel (2) charakteristischen in der Auswerteeinrichtung (4) gespeicherten Signalwerten verglichen werden.Device according to one of claims 1 to 3, characterized in that the electronic evaluation device (4) carries out a microprocessor (13) for performing a Fourier analysis of the measured sound signals of the wake-up sensor (10), and that these signal values are also used for the target (2 ) characteristic signal values stored in the evaluation device (4) can be compared. Vorrichtung nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß es sich bei dem Suchkopf (15) des Flugkörpers (14) um einen Infrarot-Suchkopf mit passivem Infrarot-Sensor handelt.Device according to one of claims 1 to 4, characterized in that the seeker head (15) of the missile (14) is an infrared seeker head with a passive infrared sensor. Vorrichtung nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß es sich bei dem Suchkopf (15) des Flugkörpers (14) um einen Radar-Suchkopf handelt.Device according to one of claims 1 to 4, characterized in that the seeker head (15) of the missile (14) is a radar seeker head.
    EP03014218A 2002-08-31 2003-06-25 Apparatus for fighting against targets Expired - Fee Related EP1394495B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    DE10240314 2002-08-31
    DE10240314A DE10240314A1 (en) 2002-08-31 2002-08-31 Target combat device

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    EP1394495A1 true EP1394495A1 (en) 2004-03-03
    EP1394495B1 EP1394495B1 (en) 2005-08-31

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    CA (1) CA2437374C (en)
    DE (2) DE10240314A1 (en)
    IL (1) IL157599A0 (en)
    NO (1) NO327291B1 (en)

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    WO2015052707A1 (en) 2013-10-08 2015-04-16 Israel Aerospace Industries Ltd. Missile system including ads-b receiver

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    EP0375872A1 (en) * 1988-12-02 1990-07-04 Atlas Elektronik Gmbh Fuze triggered by a tracked vehicle
    FR2641872A1 (en) * 1989-01-18 1990-07-20 Clausin Jacques System for locating helicopters hidden behind a screen of vegetation
    FR2678060A1 (en) * 1976-08-03 1992-12-24 France Etat Armement Method and device for selectively firing a horizontal-action weapon
    FR2728676A1 (en) * 1982-05-11 1996-06-28 France Etat Firing control system for horizontal-section pyrotechnic charge
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    FR2678060A1 (en) * 1976-08-03 1992-12-24 France Etat Armement Method and device for selectively firing a horizontal-action weapon
    DE3140728A1 (en) * 1981-10-14 1983-05-05 Messerschmitt-Bölkow-Blohm GmbH, 8000 München DEVICE FOR FIGHTING TARGETS LIKE TANKS OR THE LIKE, WITH AN AMMUNITION AIMING AT THE TARGET
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    WO2015052707A1 (en) 2013-10-08 2015-04-16 Israel Aerospace Industries Ltd. Missile system including ads-b receiver
    EP3055638A4 (en) * 2013-10-08 2016-10-26 Israel Aerospace Ind Ltd Missile system including ads-b receiver
    US10126100B2 (en) 2013-10-08 2018-11-13 Israel Aerospace Industries Ltd. Missile system including ADS-B receiver

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    EP1394495B1 (en) 2005-08-31
    IL157599A0 (en) 2004-03-28
    CA2437374C (en) 2010-10-19
    DE50301073D1 (en) 2005-10-06
    DE10240314A1 (en) 2004-03-11
    CA2437374A1 (en) 2004-02-29
    NO327291B1 (en) 2009-06-02
    NO20032967D0 (en) 2003-06-27

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