EP0727638A1 - Method and apparatus for fighting against helicopters operating under cover - Google Patents

Method and apparatus for fighting against helicopters operating under cover Download PDF

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Publication number
EP0727638A1
EP0727638A1 EP96102303A EP96102303A EP0727638A1 EP 0727638 A1 EP0727638 A1 EP 0727638A1 EP 96102303 A EP96102303 A EP 96102303A EP 96102303 A EP96102303 A EP 96102303A EP 0727638 A1 EP0727638 A1 EP 0727638A1
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Prior art keywords
target
missile
search
phase
carried out
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Granted
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EP96102303A
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German (de)
French (fr)
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EP0727638B1 (en
Inventor
Egbert Harraeus
Bernt Dr. Obkircher
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LFK Lenkflugkoerpersysteme GmbH
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Daimler Benz Aerospace AG
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    • 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
    • F41G7/2226—Homing guidance systems comparing the observed data with stored target data, e.g. target configuration data
    • 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 method and an apparatus by means of which opposing helicopters operating under cover, appearing briefly and then again using cover can be effectively combated even after the loss of line of sight, using an electro-optical seeker head selectively developed for helicopter type recognition .
  • infrared search head is used for helicopter detection.
  • the search head essentially consists of an entry optic in the focal plane of which infrared-sensitive detector elements are arranged in a rectangular matrix. Each detector element can be read out individually and the resulting signal can be examined for amplitude and frequency behavior.
  • the observation axis of the seeker head is oriented vertically downwards, whereby it can be assumed that opposing helicopters, using shadows from the terrain, move near the ground.
  • the search head is designed in such a way that it should be able to reliably recognize helicopters in a defined search area on the basis of its image field design and its height above the ground on the basis of its characteristic radiation modulated by the rotor blade movement.
  • this vertically downward-oriented sensor can be used as follows.
  • the observing shooter discovers an enemy Helicopter. It estimates the distance to the target and enters this value into the missile launch device. Since the sensor image field is limited, the success of the control measures depends crucially on the reliability of this estimate. Furthermore, it must be ensured that the search areas predetermined by the estimated values overlap.
  • the missile is launched. In accordance with the distance data and the predefined sensor image field, the missile moves in a predefined trajectory and is then braked at a height of typically 800-1200 m by a rear parachute. The longitudinal axis of the missile is oriented vertically after completion of the braking process, the target seeker looks down, the search phase begins.
  • the falling speed must be adjusted by the parachute to the performance of the signal evaluation method. If the target is detected, the parachute is disconnected. The remaining part of the missile, which contains the warhead, must now be accelerated, starting from the low falling speed, to such an extent that the target can be reliably fought even at the maximum escape speed.
  • the invention has for its object to provide a user-friendly, effective method and a device for realizing the same, with which the reliable detection and control, in particular of covertly operating helicopters, ie. H. without line of sight of the shooter to the target, without range measurement, with low missile weight is ensured, it being essential that the target search can be carried out in parallel with a flight profile in a plane or at a slight angle to the terrain.
  • the operational task is shown schematically in FIG. Based on previous observations, a shooter positioned at the starting point assumes that an enemy target behind a tree is in cover. So there is no direct line of sight between him and the target.
  • the shoulder launcher not shown here, is aligned approximately to the target, the missile launches at an elevation angle of typically 70 °. On At a height of typically 800m, the missile swings into a trajectory that runs approximately parallel to the terrain.
  • the search phase now begins, the details of which can be seen in FIG. 2. Due to the angular position of the stationary wedge K and the rotary wedge DK, the image field axis is oriented downwards at an angle of typically 45 °.
  • the detector matrix DM e.g. InSb detector matrix with 256 * 256 individual detectors
  • the design of the lens system LS at a flight altitude of 800 m on the surface of the earth, a search strip with a width (perpendicular to the direction of flight) of up to 1200 is typically found m trained.
  • the missile If a target is discovered on the basis of its infrared intrinsic radiation, which is uniquely modulated by the Rortor blade movements, the missile, as indicated in FIG. 3, approaches the target according to the steering law of proportional navigation. At the same time, the rotary wedge rotates 180 ° about the missile longitudinal axis, so that the image field axis is now collinearly oriented to the missile axis. This is the start of the pursuit phase.
  • the signal evaluation SAW is used for lane formation. This improves the prediction of the target movement and the accuracy of the hit. Furthermore, the measured values of a position sensor (roll, pitch and yaw movements) are used in the signal evaluation for image stabilization.
  • the rotary and longitudinal movements of the missile will be detected quantitatively by sensors and the field of view on the ground will be electronically stabilized by means of suitable algorithms so that the frequency detection of the helicopter takes place within grid elements of a laser coordinate system resting on the ground.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Optical Radar Systems And Details Thereof (AREA)

Abstract

The method is carried out using an aircraft with an integral target search head. The individual radiation of the helicopter modulated by the movement of the rotor blade is used to identify the target. The aircraft containing the search head traverses a flight path parallel to the earth's surface during a search phase. The line of sight axis during the search phase is at a downwards, acute angle. While pursuing the target, the line of sight axis is colinear with the aircraft axis. The rotary and longitudinal movement of the aircraft is quantitatively detected by sensors. Using suitable algorithms, the field of view on the ground is stabilised electronically so that the frequency identification of the helicopter, which requires a still picture in the search head for a given min. time, is carried out within raster elements of a ground coordinate system.

Description

Die Erfindung bezieht sich auf ein Verfahren und eine Vorrichtung, mit deren Hilfe verdeckt operierende, kurzeitig auftauchende und anschließend wieder die Deckung nutzende gegnerische Hubschrauber auch nach dem Verlust der Sichtverbindung unter Verwendung eines selektiv auf Hubschrauber-Typenerkennung entwickelten elektro-optischen Suchkopfes wirksam bekämpft werden können.The invention relates to a method and an apparatus by means of which opposing helicopters operating under cover, appearing briefly and then again using cover can be effectively combated even after the loss of line of sight, using an electro-optical seeker head selectively developed for helicopter type recognition .

Solche Vorrichtungen sind in unterschiedlichen Ausführungsformen bekannt. Als Beispiel hierfür kann die Patentschrift DE 37 33 681 C1 genannt werden. Bei der bekannten Vorrichtung wird zur Hubschrauberdetektion ein sog. Infrarot-Suchkopf verwendet. Der Suchkopf besteht im wesentlichen aus einer Eintrittsoptik in deren Brennebene infrarot-empfindliche Detektorelemente in einer Rechtecksmatrix angeordnet sind. Jedes Detektorelement kann individuell ausgelesen, das daraus resultierende Signal nach Amplitude und Frequenzverhalten untersucht werden.Such devices are known in different embodiments. The patent DE 37 33 681 C1 can be mentioned as an example of this. In the known device, a so-called infrared search head is used for helicopter detection. The search head essentially consists of an entry optic in the focal plane of which infrared-sensitive detector elements are arranged in a rectangular matrix. Each detector element can be read out individually and the resulting signal can be examined for amplitude and frequency behavior.

Die Beobachtungsachse des Suchkopfes ist vertikal nach unten ausgerichtet, wobei davon ausgegangen werden kann, daß gegnerische Hubschrauber, Geländeabschattungen nutzend, sich in Bodennähe bewegen. Der Suchkopf ist so ausgestaltet, daß er aufgrund seiner Bildfeldauslegung und seiner Höhe über Grund Hubschrauber anhand ihrer durch die Rotorblattbewegung charakteristisch modulierten Eigenstrahlung in einem definierten Suchgebiet zuverlässig erkennen können soll.The observation axis of the seeker head is oriented vertically downwards, whereby it can be assumed that opposing helicopters, using shadows from the terrain, move near the ground. The search head is designed in such a way that it should be able to reliably recognize helicopters in a defined search area on the basis of its image field design and its height above the ground on the basis of its characteristic radiation modulated by the rotor blade movement.

Die Auslegung des Suchkopfes auf die vertikale Beobachtungsrichtung schränkt die operationelle Leistungsfähigkeit eines mit diesem Sensor ausgestatteten Abwehrflugkörpers erheblich ein, insbesondere wenn dieser "schulterverschießbar" sein muß. Kriterien für die Schulterverschießbarkeit sind geringes Gewicht (typisch 12 kg), einfache Handhabung, hohe Zuverlässigkeit und ein günstiges Kosten/Nutzenverhältnis.The design of the seeker head on the vertical direction of observation considerably limits the operational performance of a defense missile equipped with this sensor, especially if it has to be "shoulder-lockable". The criteria for shoulder lockability are low weight (typically 12 kg), easy handling, high reliability and a favorable cost / benefit ratio.

In Verbindung mit einem Flugkörper kann dieser vertikal nach unten ausgerichtete Sensors wie folgt eingesetzt werden. Der beobachtende Schütze entdeckt einen gegnerischen Hubschrauber. Er schätzt die Entfernung zum Ziel und gibt diesen Wert in die Startvorrichtung des Flugkörpers ein. Da das Sensorbildfeld begrenzt ist, hängt von der Zuverlässigkeit dieser Schätzung der Erfolg der Bekämpfungsmaßnahine entscheidend ab. Ferner muß sichergestellt sein, daß sich die durch die Schätzwerte vorgegebenen Suchbereiche überlappen. Der Flugkörper wird gestartet. Entsprechend der Entfernungsdaten und des vorgegebenen Sensorbildfeldes bewegt sich der Flugkörper auf einer vorgegebenen Flugbahn um dann auf einer Höhe von typischerweise 800 - 1200 m durch einen Heckfallschirm abgebremst zu werden. Die Flugkörperlängsachse ist nach Abschluß des Bremsvorganges vertikal orientiert, der Zielsuchkopf blickt nach unten, die Suchphase beginnt. Die Fallgeschwindigkeit muß durch den Fallschirm der Leistungsfähigkeit des Signalauswerteverfahrens angepaßt werden. Ist das Ziel erfaßt, wird der Fallschirm abgetrennt. Der verbliebene Teil des Flugkörpers, der den Gefechtkopf beinhaltet, muß nunmehr, ausgehend von der geringen Fallgeschwindigkeit, soweit beschleunigt werden, daß das Ziel selbst bei maximaler Fluchtgeschwindigkeit zuverlässig bekämpft werden kann.In conjunction with a missile, this vertically downward-oriented sensor can be used as follows. The observing shooter discovers an enemy Helicopter. It estimates the distance to the target and enters this value into the missile launch device. Since the sensor image field is limited, the success of the control measures depends crucially on the reliability of this estimate. Furthermore, it must be ensured that the search areas predetermined by the estimated values overlap. The missile is launched. In accordance with the distance data and the predefined sensor image field, the missile moves in a predefined trajectory and is then braked at a height of typically 800-1200 m by a rear parachute. The longitudinal axis of the missile is oriented vertically after completion of the braking process, the target seeker looks down, the search phase begins. The falling speed must be adjusted by the parachute to the performance of the signal evaluation method. If the target is detected, the parachute is disconnected. The remaining part of the missile, which contains the warhead, must now be accelerated, starting from the low falling speed, to such an extent that the target can be reliably fought even at the maximum escape speed.

Die Nachteile der bekannten Einrichtung hinsichtlich der Wirksamkeit eines Waffensystems sind offenkundig:

  • Falsche Entfernungsschätzung führt zu Fehlschuß, was nur durch einen zusätzlich eingesetzten Laserentfernungsmesser vermeidbar wäre.
  • Die Suchphase erfolgt bei geringer Flugkörpergeschwindigkeit. In der daraus resultierenden Zeit kann das Ziel eine zusätzliche Distanz zurücklegen, deren Überwindung erhöhte Anforderungen an die Zielverfolgungsgeschwindigkeit des Flugkörpers stellt.
  • Aufgrund der ungünstigen Energiebilanz durch zusätzliche Brems- und Beschleunigungsmanöver erhöhter Treibstoffbedarf, und daraus resultierend Gewichtszunahme, ungünstiges Kosten-/Nutzenverhältnis.
  • Der Fallschirm erhöht Komplexität des Flugkörpers und damit dessen Ausfallquote, sowie die Herstellungskosten.
  • Ohne eine zusätzliche Vorrichtung zur elektronischen oder mechanischen Bildstabilisierung im Suchkopf können die Pendelbewegungen am Fallschirm während der Suchphase nicht ausgeglichen werden, so daß die Frequenz der Hubschrauberstrahlung in der Realität - so wie in DE 37 33 681 C1 angegeben - gar nicht erkannt werden kann.
The disadvantages of the known device with regard to the effectiveness of a weapon system are obvious:
  • Incorrect range estimation leads to miss, which could only be avoided by using an additional laser range finder.
  • The search phase takes place at low missile speeds. In the resulting time, the target can cover an additional distance, the overcoming of which places increased demands on the target velocity of the missile.
  • Due to the unfavorable energy balance due to additional braking and acceleration maneuvers, increased fuel consumption and the resulting weight gain, unfavorable cost / benefit ratio.
  • The parachute increases the complexity of the missile and thus its failure rate, as well as the manufacturing costs.
  • The pendulum movements on the parachute can be carried out without an additional device for electronic or mechanical image stabilization in the seeker head cannot be compensated during the search phase, so that the frequency of the helicopter radiation cannot be recognized in reality, as stated in DE 37 33 681 C1.

Der Erfindung liegt die Aufgabe zugrunde, ein bedienerfreundliches, wirksames Verfahren und eine Einrichtung zur Realisierung desselben aufzuzeigen, mit dem die zuverlässige Erkennung und Bekämpfung insbesondere von verdeckt operierenden Hubschraubern, d. h. ohne Sichtverbindung des Schützen zum Ziel, ohne Entfernungsmessung, bei niedrigem Flugkörpergewicht gewährleistet ist, wobei wesentlich ist, daß die Zielsuche auch bei einem Flugprofil in einer Ebene parallel oder unter einem geringen Neigungswinkel zum Gelände erfolgen kann.The invention has for its object to provide a user-friendly, effective method and a device for realizing the same, with which the reliable detection and control, in particular of covertly operating helicopters, ie. H. without line of sight of the shooter to the target, without range measurement, with low missile weight is ensured, it being essential that the target search can be carried out in parallel with a flight profile in a plane or at a slight angle to the terrain.

Diese Aufgabe wird durch die im Anspruch 1 aufgezeigten Maßnahmen gelöst. In den Unteransprüchen sind Ausgestaltungen und Weiterbildungen angegeben und in der nachfolgenden Beschreibung wird wird anhand eines Bekämpfungsszenarios ein Ausfühungsbeispiel erläutert und in den Figuren der Zeichnung, die auch als Ergänzung der Beschreibung anzusehen sind, skizziert.This object is achieved by the measures indicated in claim 1. Refinements and developments are specified in the subclaims and in the following description an exemplary embodiment is explained on the basis of a control scenario and outlined in the figures of the drawing, which are also to be regarded as a supplement to the description.

Die Erfindung wird nachfolgend anhand der Figuren Fig. 1 bis Fig. 3 erläutert. Es zeigen

Fig. 1
in schematischer Darstellung die operationelle Aufgabe gemäß der Erfindung,
Fig. 2
in schematischer Darstellung die Suchphase gemäß der Erfindung, und
Fig. 3
in schematischer Darstellung die Zielverfolgungsphase gemäß der Erfindung.
The invention is explained below with reference to FIGS. 1 to 3. Show it
Fig. 1
a schematic representation of the operational task according to the invention,
Fig. 2
in a schematic representation the search phase according to the invention, and
Fig. 3
the target tracking phase according to the invention in a schematic representation.

In Fig. 1 ist die operationelle Aufgabe schematisch dargestellt. Ein am Startpunkt positionierter Schütze geht aufgrund vorangegangener Beobachtungen davon aus, daß sich ein gegnerisches Zielobjekt hinter einem Baum in Deckung befindet. Damit besteht zwischen ihm und dem Ziel keine direkte Sichtverbindung. Die hier nicht näher dargestellte Schulter-Startvorrichtung wird ungefähr zum Ziel ausgerichtet, der Flugkörper startet unter einem Elevationswinkel von typischerweise 70°. Auf einer Höhe von typischerweise 800m schwenkt der Flugkörper in eine Flugbahn ein, die ungefähr parallel zum Gelände verläuft.The operational task is shown schematically in FIG. Based on previous observations, a shooter positioned at the starting point assumes that an enemy target behind a tree is in cover. So there is no direct line of sight between him and the target. The shoulder launcher, not shown here, is aligned approximately to the target, the missile launches at an elevation angle of typically 70 °. On At a height of typically 800m, the missile swings into a trajectory that runs approximately parallel to the terrain.

Nunmehr beginnt die Suchphase, deren Details aus Fig. 2 ersichtlich werden. Die Bildfeldachse wird aufgrund der Winkelstellung des stationären Keiles K und des Drehkeiles DK unter einem Winkel von typischerweise 45° nach unten ausgerichtet. Durch die Wahl der Detektormatrix DM(z. B. InSb-Detektormatrix mit 256*256 Einzeldetektoren) und der Auslegung des Linsensystems LS wird bei einer Flughöhe von 800 m auf der Erdoberfläch typischerweise ein Suchstreifen der Breite (senkrecht zur Flugrichtung) von bis zu 1200 m ausgebildet.The search phase now begins, the details of which can be seen in FIG. 2. Due to the angular position of the stationary wedge K and the rotary wedge DK, the image field axis is oriented downwards at an angle of typically 45 °. By choosing the detector matrix DM (e.g. InSb detector matrix with 256 * 256 individual detectors) and the design of the lens system LS, at a flight altitude of 800 m on the surface of the earth, a search strip with a width (perpendicular to the direction of flight) of up to 1200 is typically found m trained.

Wird ein Ziel aufgrund seiner durch die Rortorblattbewegungen in eindeutiger Weise modulierten Infrarot-Eigenstrählung entdeckt, so nähert sich der Flugkörper, wie in Fig. 3 angedeutet, dem Ziel nach dem Lenkgesetz der Proportionalnavigation. Gleichzeitig dreht sich der Drehkeil um 180° um die Flugkörper-Längsachse, so daß die Bildfeldachse nunmehr kollinear zur Flugkörperachse orientiert ist. Damit beginnt die Zielverfolgungsphase.If a target is discovered on the basis of its infrared intrinsic radiation, which is uniquely modulated by the Rortor blade movements, the missile, as indicated in FIG. 3, approaches the target according to the steering law of proportional navigation. At the same time, the rotary wedge rotates 180 ° about the missile longitudinal axis, so that the image field axis is now collinearly oriented to the missile axis. This is the start of the pursuit phase.

Neben der Zielsuche und eindeutigen Zielerkennung dient die Signalauswertung SAW der Spurbildung. Dadurch verbessert sich die Prädiktion der Zielbewegung und die Treffergenauigkeit. Desweiteren werden die Meßwerte eines Lagesensors (Roll-, Nick- und Gierbewegungen) in der Signalauswertung zur Bildstabitisierung verwendet. Dabei werden die Dreh- und Längsbewegungen des Flugkörpers durch Sensoren quantitativ erfaßt werden und mittels geeigneter Algorithmen das Sehfeld am Boden auf elektronischem Wege so stabilisiert, daß die Frequenzerkennung der Hubschrauber innerhalb von Rasterelementen eines am Boden ruhenden Laserkoordinatensystems erfolgt.In addition to the target search and clear target recognition, the signal evaluation SAW is used for lane formation. This improves the prediction of the target movement and the accuracy of the hit. Furthermore, the measured values of a position sensor (roll, pitch and yaw movements) are used in the signal evaluation for image stabilization. The rotary and longitudinal movements of the missile will be detected quantitatively by sensors and the field of view on the ground will be electronically stabilized by means of suitable algorithms so that the frequency detection of the helicopter takes place within grid elements of a laser coordinate system resting on the ground.

Claims (6)

Verfahren zum lückenlosen Erfassen, Identifizieren und zuverlässigen Bekämpfen verdeckt operierender Hubschrauben mit einem Flugkörper mit integriertem Zielsuchkopf, wobei die durch die Rotorblattbewegung modulierte Eigenstrahlung des Hubschraubers zur Zielerkennung genutzt wird,
dadurch gekennzeichnet, - daß der den Zielsuchkopf beinhaltende Flugkörper während der Suchphase eine zur Erdoberfläche in etwa parallele Flugbahn ausführt, - daß die Sichtlinienachse während der Suchphase mit einem geeigneten Winkel schräg nach unten weist und während der Zielverfolgung kollinear zur Flugkörperachse verläuft, - daß die Suche typischerweise in einem Streiten von bis zu 1200 m Breite erfolgt, - daß die Dreh- und Längsbewegungen des Flugkörpers durch Sensoren quantitativ erfaßt werden und - daß mittels geeigneter Algorithmen das Sehfeld am Boden auf elektronischem Wege so stabilisiert wird, daß die Frequenzerkennung der Hubschrauber, die ein über eine gewisse Mindestzeit ruhendes Bild im Suchkopf erfordert, innerhalb von Rasterelementen eines am Boden ruhenden Koordinatensystems erfolgt. Process for the complete detection, identification and reliable combat of concealed operating helicopters with a missile with an integrated target seeker head, the helicopter's own radiation modulated by the rotor blade movement being used for target recognition,
characterized by that the missile containing the target seeker executes an approximately parallel trajectory to the earth's surface during the search phase, that the line of sight axis points obliquely downward at a suitable angle during the search phase and is collinear with the missile axis during target tracking, - that the search is typically carried out in a dispute up to 1200 m wide, - That the rotational and longitudinal movements of the missile are detected quantitatively by sensors and - That the field of view on the ground is electronically stabilized by means of suitable algorithms so that the frequency detection of the helicopter, which requires a picture that is stationary for a certain minimum time in the seeker head, takes place within raster elements of a coordinate system resting on the ground. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß das Sensorbildfeld nach erfolgter Zielerkeunung durch eine Veränderung der Sichtlinienachse den Anforderungen der Zielverfolgungsphase angepaßt wird.Method according to Claim 1, characterized in that the sensor image field is adapted to the requirements of the target tracking phase after the target has been identified by changing the line of sight axis. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß die Bildfeldadaption des Infrarot-Zielsuchkopfes beim Übergang von der Suchphase zur Zielverfolgungsphase durch optisch wirksame Drehkeile erfolgt.Method according to Claim 1, characterized in that the image field adaptation of the infrared target seeker head is carried out by optically effective rotary wedges during the transition from the search phase to the target tracking phase. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß die Bildfeldadaption durch eine mechanisch definierte, variable Anordnung von Spiegeln erfolgt.Method according to claim 1, characterized in that the image field adaptation is carried out by a mechanically defined, variable arrangement of mirrors. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß aus dem zeitlichen Ablauf der Zielbewegung (Spurbildung) in der Endphase der Zielverfolgung der optimale Auftreffbereich des Flugkörpers im Ziel berechnet wird.Method according to Claim 1, characterized in that the optimal impact area of the missile in the target is calculated from the time sequence of the target movement (formation of lanes) in the final phase of target tracking. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß der Sensor auf einer Flugbahn bewegt wird, die näherungsweise senkrecht zu der Richtung verläuft, in der das Ziel ursprünglich geortet wurde.Method according to claim 1, characterized in that the sensor is moved on a trajectory which is approximately perpendicular to the direction in which the target was originally located.
EP96102303A 1995-02-20 1996-02-16 Method and apparatus for fighting against helicopters operating under cover Expired - Lifetime EP0727638B1 (en)

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Application Number Priority Date Filing Date Title
DE19505791 1995-02-20
DE19505791A DE19505791C1 (en) 1995-02-20 1995-02-20 Method and device for combating covertly operating helicopters

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EP0727638A1 true EP0727638A1 (en) 1996-08-21
EP0727638B1 EP0727638B1 (en) 2001-07-11

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DE19505791C1 (en) 1996-08-14
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DE59607243D1 (en) 2001-08-16

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