EP1394495B1 - Apparatus for fighting against targets - Google Patents

Apparatus for fighting against targets Download PDF

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Publication number
EP1394495B1
EP1394495B1 EP03014218A EP03014218A EP1394495B1 EP 1394495 B1 EP1394495 B1 EP 1394495B1 EP 03014218 A EP03014218 A EP 03014218A EP 03014218 A EP03014218 A EP 03014218A EP 1394495 B1 EP1394495 B1 EP 1394495B1
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EP
European Patent Office
Prior art keywords
target
sensor
missile
search head
acoustic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
EP03014218A
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German (de)
French (fr)
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EP1394495A1 (en
Inventor
Ralf-Joachim Dr. Herrmann
Wolfgang Dr. Seidel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rheinmetall Waffe Munition GmbH
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Rheinmetall Waffe Munition GmbH
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Publication date
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Publication of EP1394495A1 publication Critical patent/EP1394495A1/en
Application granted granted Critical
Publication of EP1394495B1 publication Critical patent/EP1394495B1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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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 controlling targets within a area to be monitored with a terrestrial directional launcher, a target detection device connected to the launcher and at least one shootable from the launcher Missiles.
  • From DE 31 40 728 C2 is known, for example, to combat An accurate determination of the destination by a combination of tanks make passive and active sensors.
  • passive ones Sensors e.g., acoustic sensors
  • the active sensors for determining the target speed. From the Changing the target direction and the target speed can then be the trajectory of the target and thus also the firing time of the missile be determined.
  • the invention is based on the object, a device of the above specify the type mentioned, which is simple and inexpensive, a short Has reaction time and their launcher and target detection device by the use of appropriate sensors is not locatable.
  • the invention is based essentially on the idea that the device a target detection device comprising exclusively passive sensors used and the only the direction, but not the trajectory of the target to be attacked before the missile launches determined, and that the missile of the device has a seeker that after Launch of the missile in targeting direction (for example by means of an infrared sensor) autonomously seeks the destination and then destroys it.
  • a locatable connection between the Missile and the launcher or the target detection device does not exist during the flight phase of the missile.
  • the device according to the invention has the advantage that they are relatively small autonomous unit e.g. manually within an area to be monitored is installable and monitors the corresponding room area for a long time.
  • the device is equipped with e.g. acoustic alarm sensor provided.
  • the Target detection device then performs a permanent frequency analysis of received acoustic signals. Once the acoustic frequency spectrum indicates a target to be attacked, the direction sensor is activated and the Bearing angle to the target determined.
  • the launcher is in the direction of bearing and the missile (e.g., a "stinger" missile) is launched. Of the Infrared sensor of the rocket then seeks a heat source (target) in the through the acoustic bearing certain space segment, and the rocket is using a corresponding steering device guided in the target.
  • the acoustic Bearing sensor at least four microphones, each at the vertices of a Tetrahedrons are arranged.
  • the wake-up sensor is one of the microphones of the Peilsensors.
  • FIGS. 1 and 2 denotes a device according to the invention for controlling of helicopters 2 within a given space to be monitored designated.
  • the device 1 consists of a housing 3 in which both a Energy supply unit and an electronic evaluation device 4 a target detection device 5 is housed (see also Fig.3).
  • a straightening system 6 adjoins the housing 3, by means of which a launcher 7 can be directed in azimuth and elevation.
  • three legs 8 are arranged laterally, which are located on the Support ground 9 and where three microphones 10 of an acoustic Bearing sensor 11 are attached.
  • a fourth microphone 10 of the acoustic directional sensor 11 is arranged on the straightener 6, so that the four microphones 10 of the Bearing sensor 11 form the vertices of a tetrahedron. All 10 microphones Peilsensors 11 are via electrical lines 12 with the electronic Evaluation device 4 connected. This contains a microprocessor 13.
  • At least one missile 14 is arranged, which with a homing IR seeker 15 and a not shown Is provided steering device.
  • the device 1 After setting up the device 1, this is eirgeschaitet. After that is the device 1 first in a so-called. Lauschmodus, i. it is only one acoustic wake-up circuit connected to only one of the microphones 10, activated.
  • the electronic evaluation device 4 permanently performs a fast Fourier transform (FFT) of each measured by the microphone 10 acoustic signal through. Once the frequency spectrum of the acoustic Signature of a helicopter is similar, the target detection device in the so-called DF mode offset.
  • FFT fast Fourier transform
  • the launcher 7 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 Seeker head 15 of the missile 14 cooled to operating temperature and a Friend-enemy identification queried and shot down the missile 14 in an enemy case.
  • the missile 14 is accelerated to supersonic speed and the IR seeker head 15 seeks a target (heat source) in the space segment that passes through the acoustic bearing was determined. After detection of the goal 2 becomes the Missile 14 guided by means of IR seeker head 15 and steering device to the target.
  • a target heat source
  • the invention is not limited to the one described above Embodiment limited. So it may be at the seeker of the Missile also act around a radar seeker head.
  • the missile is fired only when the seeker already before the launch of the missile, the target in the by the acoustic bearing has detected defined spatial segment.

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

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 Zielerfassungseinrichtung und mindestens einem aus der Abschußeinrichtung verschießbaren Flugkörper.The invention relates to a device for controlling targets within a area to be monitored with a terrestrial directional launcher, a target detection device connected to the launcher and at least one shootable 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 Zielgeschwindigkeit kann dann die Bewegungsbahn des Zieles und damit auch der Abfeuerzeitpunkt des Flugkörpers ermittelt werden.From DE 31 40 728 C2 is known, for example, to combat An accurate determination of the destination by a combination of tanks make passive and active sensors. Here serve the passive ones Sensors (e.g., acoustic sensors) for determining the respective target direction and the active sensors for determining the target speed. From the Changing the target direction and the target speed can then be 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 zielcharakteristischen Signale 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, inter alia, that for the Path determination of the target and the subsequent judging of the launcher the missile takes a relatively long time, so that the reaction time of Device from the reception of the acoustic target-characteristic signals to the Firing the missile for fighting very fast targets, such as from Helicopters, too long. It also exists through the use of the active Sensors of the target detection device the risk that the opponent ground-based Launcher can destroy and destroy.

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 is based on the object, a device of the above specify the type mentioned, which is simple and inexpensive, a short Has reaction time and their launcher and target detection device by the use of appropriate sensors is not locatable.

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. Further, particularly advantageous embodiments of the invention reveal the dependent claims.

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 based essentially on the idea that the device a target detection device comprising exclusively passive sensors used and the only the direction, but not the trajectory of the target to be attacked before the missile launches determined, and that the missile of the device has a seeker that after Launch of the missile in targeting direction (for example by means of an infrared sensor) autonomously seeks the destination and then destroys it. A locatable connection between the Missile and the launcher or the target detection 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 they are relatively small autonomous unit e.g. manually within an area to be monitored is installable and monitors the corresponding room area for a long time. For this, the device is equipped with e.g. acoustic alarm sensor provided. The Target detection device then performs a permanent frequency analysis of received acoustic signals. Once the acoustic frequency spectrum indicates a target to be attacked, the direction sensor is activated and the Bearing angle to the target determined. The launcher is in the direction of bearing and the missile (e.g., a "stinger" missile) is launched. Of the Infrared sensor of the rocket then seeks a heat source (target) in the through the acoustic bearing certain space segment, and the rocket is using a corresponding steering device guided in 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 comprises the acoustic Bearing sensor at least four microphones, each at the vertices of a Tetrahedrons are arranged.

Vorzugsweise handelt es sich bei dem Wecksensor um eines der Mikrophone des Peilsensors.Preferably, the wake-up sensor is 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 will become apparent from the following with reference to figures explained embodiments. Show it:
  • 1 shows a schematic side view of a device according to the invention for controlling air targets;
  • A plan view of the device shown in Figure 1 and
  • 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).In FIGS. 1 and 2, 1 denotes a device according to the invention for controlling of helicopters 2 within a given space to be monitored designated. The device 1 consists of a housing 3 in which both a Energy supply unit and an electronic evaluation device 4 a target detection device 5 is housed (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.On the upper side, a straightening system 6 adjoins the housing 3, by means of which a launcher 7 can be directed 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 are located on the Support ground 9 and where three microphones 10 of an acoustic Bearing sensor 11 are attached. A fourth microphone 10 of the acoustic directional sensor 11 is arranged on the straightener 6, so that the four microphones 10 of the Bearing sensor 11 form the vertices of a tetrahedron. All 10 microphones Peilsensors 11 are via electrical lines 12 with the electronic 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.In the launcher 7 at least one missile 14 is arranged, which with a homing IR seeker 15 and a not shown Is provided steering device.

    Nachfolgend wird auf die Funktionsweise der erfindungsgemäßen Vorrichtung eingegangen.The following will discuss the operation of the device according to the invention 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 setting up the device 1, this is eirgeschaitet. After that is the device 1 first in a so-called. Lauschmodus, i. it is only one acoustic wake-up circuit connected to only one of the microphones 10, activated. The electronic evaluation device 4 permanently performs a fast Fourier transform (FFT) of each measured by the microphone 10 acoustic signal through. Once the frequency spectrum of the acoustic Signature of a helicopter is similar, the target detection device in the so-called DF mode offset.

    Im Peilmodus 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 Peilmodus all four microphones 10 are activated and the electronic Evaluation device 4 determines the spatial direction to the destination 2. For this purpose become the coming of the target 2 acoustic signals from the microphones 10 measured with a time lag. From this phase shift is then using 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 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 Seeker head 15 of the missile 14 cooled to operating temperature and a Friend-enemy identification queried and shot down the missile 14 in an enemy case.

    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 seeks a target (heat source) in the space segment that passes through the acoustic bearing was determined. After detection of the goal 2 becomes the Missile 14 guided by means of IR seeker head 15 and steering device to the target.

    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.Of course, the invention is not limited to the one described above Embodiment limited. So it may be at the seeker of the Missile also act around a radar seeker head.

    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 case of using a passive IR seeker head can also be provided that the missile is fired only when the seeker already before the launch of the missile, the target in the by the acoustic bearing has detected defined spatial segment.

    BezugszeichenlisteLIST OF REFERENCE NUMBERS

    11
    Vorrichtungcontraption
    22
    Ziel, HubschrauberTarget, 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, wake-up sensor
    1111
    Peilsensorbearing sensor
    1212
    elektrische Leitungelectrical line
    1313
    Mikroprozessormicroprocessor
    1414
    Flugkörpermissile
    1515
    Suchkopfseeker

    Claims (6)

    1. Apparatus for attacking targets (2) within an area to be monitored, having a firing device (7), which is ground-based and can be aimed, having a target detection device (5) which is connected to the firing device (7), and having at least one missile (14) which can be fired from the firing device (7), having the following features:
      a) the missile (14) has a target-seeking search head (15);
      b) the target detection device (5) has an electronic evaluation device (4), a passive, acoustic wake-up sensor (10) which is connected to the evaluation device (4), and a passive acoustic direction-finding sensor (11), which is connected to the evaluation apparatus (4), for determination of the target direction;
      c) the individual assemblies of the apparatus (1) are operatively connected to one another in such a way that the electronic evaluation device (4) activates the direction-finding sensor (11) by means of the wake-up sensor (10) after receiving signals which are characteristic of a target, determines signal values for alignment of the firing device in the target direction, and drives the appropriate control drives for the aiming system (6) for the firing device (7), and in that the missile (14) is then fired in the target direction, and locates the target autonomously using its search head (15).
    2. Apparatus according to Claim 1, characterized in that the acoustic direction-finding sensor (11) has at least four microphones (10), which are each arranged at the corners of a tetrahedron.
    3. Apparatus 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).
    4. Apparatus according to one of Claims 1 to 3, characterized in that the electronic evaluation device (4) is a microprocessor (13) for carrying out a Fourier analysis of the measured sound signals from the wake-up sensor (10), and in that these signal values are compared with signal values which are characteristic of the target (2) and are stored in the evaluation device (4).
    5. Apparatus according to one of Claims 1 to 4, characterized in that the search head (15) of the missile (14) is an infrared search head with a passive infrared sensor.
    6. Apparatus according to one of Claims 1 to 4, characterized in that the search head (15) of the missile (14) is a radar search 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
    DE10240314A DE10240314A1 (en) 2002-08-31 2002-08-31 Target combat device
    DE10240314 2002-08-31

    Publications (2)

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

    Family

    ID=27675207

    Family Applications (1)

    Application Number Title Priority Date Filing Date
    EP03014218A Expired - Fee Related EP1394495B1 (en) 2002-08-31 2003-06-25 Apparatus for fighting against targets

    Country Status (5)

    Country Link
    EP (1) EP1394495B1 (en)
    CA (1) CA2437374C (en)
    DE (2) DE10240314A1 (en)
    IL (1) IL157599A0 (en)
    NO (1) NO327291B1 (en)

    Families Citing this family (1)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    IL228789A (en) 2013-10-08 2016-03-31 Israel Aerospace Ind Ltd Missile system including ads-b receiver

    Family Cites Families (6)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR2678060B1 (en) * 1976-08-03 1994-05-20 Etat Francais Delegue Armement METHOD AND APPARATUS FOR SELECTIVE FIRE OF HORIZONTAL ACTION WEAPON.
    DE3140728C2 (en) * 1981-10-14 1985-02-07 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Device for combating targets, such as tanks or the like.
    FR2728676B1 (en) * 1982-05-11 1997-03-21 France Etat HORIZONTAL-ACTION PYROTECHNIC CHARGE FIRE CONTROL SYSTEM
    DE3840732A1 (en) * 1988-12-02 1990-06-07 Krupp Atlas Elektronik Gmbh WAKE-UP DEVICE RESPECTING CHAIN VEHICLES
    FR2641872B1 (en) * 1989-01-18 1991-10-11 Clausin Jacques SYSTEM FOR LOCATING HIDDEN HELICOPTERS BEHIND A PLANT SCREEN
    DE19906970C2 (en) * 1999-02-19 2003-03-27 Rheinmetall W & M Gmbh reconnaissance probe

    Also Published As

    Publication number Publication date
    EP1394495A1 (en) 2004-03-03
    NO20032967D0 (en) 2003-06-27
    CA2437374C (en) 2010-10-19
    CA2437374A1 (en) 2004-02-29
    DE50301073D1 (en) 2005-10-06
    IL157599A0 (en) 2004-03-28
    NO327291B1 (en) 2009-06-02
    DE10240314A1 (en) 2004-03-11

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