EP0727638B1 - Verfahren und Vorrichtung zur Bekämpfung verdeckt operierender Hubschrauber - Google Patents
Verfahren und Vorrichtung zur Bekämpfung verdeckt operierender Hubschrauber Download PDFInfo
- Publication number
- EP0727638B1 EP0727638B1 EP96102303A EP96102303A EP0727638B1 EP 0727638 B1 EP0727638 B1 EP 0727638B1 EP 96102303 A EP96102303 A EP 96102303A EP 96102303 A EP96102303 A EP 96102303A EP 0727638 B1 EP0727638 B1 EP 0727638B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- missile
- target
- image
- search
- phase
- 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 - Lifetime
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Classifications
-
- 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 with the aid of which operating under cover, appearing briefly and then covering again using enemy helicopters even after losing line of sight using a selectively designed on helicopter type recognition electro-optical seeker head can be effectively combated.
- Such devices are known in different embodiments.
- the patent specification DE 37 33 681 C1 can be mentioned as an example of this.
- the search head essentially consists of an entry optic in their Focal plane infrared-sensitive detector elements arranged in a rectangular matrix are. Each detector element can be read out individually, the resulting one Signal to be examined according to amplitude and frequency behavior.
- the observation axis of the seeker head is oriented vertically downwards, whereby it can be assumed that enemy helicopters, shadowing of the terrain using moving close to the ground.
- the search head is designed so that he helicopter due to its field of view design and its height above ground based on their characteristic radiation modulated by the rotor blade movement should be able to reliably recognize in a defined search area.
- the design of the seeker head on the vertical direction of observation limits the operational performance of a defense missile equipped with this sensor considerably, especially if it is "shoulder lockable" got to.
- the criteria for shoulder lockability are light weight (typically 12 kg), easy handling, high reliability and a favorable cost / benefit ratio.
- Sensors are used as follows.
- the observing shooter discovers an enemy Helicopter. He estimates the distance to the target and gives this value into the launch device of the missile. Since the sensor image field is limited, The success of the control measure depends on the reliability of this estimate crucially. It must also be ensured that the Predefined search ranges overlap.
- the missile is launched. Moved according to the distance data and the specified sensor image field the missile is in a predetermined trajectory and then at a height of typically to be braked 800 - 1200 m by a rear parachute.
- the missile longitudinal axis 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 process become. If the target is detected, the parachute is disconnected. The remaining one Part of the missile containing the warhead must now proceed from the low falling speed, so far accelerated that the target itself can be reliably fought at maximum escape speed.
- the invention has for its object a user-friendly, effective Show method and a device for realizing the same with the reliable detection and control, especially of covertly operating Helicopters, d. H. without line of sight of the shooter to the target, without distance measurement, is guaranteed at low missile weight, being essential is that the search for a destination is parallel or even in the case of a flight profile in one plane can be done at a slight angle to the terrain.
- the operational task is shown schematically in FIG. One at the starting point Based on previous observations, the positioned shooter assumes that an enemy target is under cover behind a tree. In order to there is no direct line of sight between him and the target. Not here shoulder starting device shown in more detail 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, which runs approximately parallel to the site.
- 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 aligned at an angle of typically 45 ° downwards.
- 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 approaches how indicated in Fig. 3, the goal according to the steering law of proportional navigation.
- the rotary wedge rotates 180 ° around the longitudinal axis of the missile, so that the image field axis is now collinearly oriented to the missile axis. That starts the pursuit phase.
- the signal evaluation also serves SAW of lane formation. This improves the prediction of the target movement and hit accuracy.
- the measured values are one Position sensors (roll, pitch and yaw movements) in the signal evaluation used for image stabilization.
- the rotational and longitudinal movements of the missile can be detected quantitatively by sensors and by means of suitable Algorithms electronically stabilize the field of view on the ground, that the frequency detection of the helicopter within grid elements a laser coordinate system resting on the ground.
Landscapes
- 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)
Description
- 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.
- 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.
Claims (4)
- Verfahren zum lückenlosen Erfassen, Identifizieren und zuverlässigen Bekämpfen verdeckt operierender Hubschrauber 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 Bildfeldachse 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 Streifen von bis zu 1200 m Breite erfolgt,daß die Dreh- und Längsbewegungen des Flugkörpers durch Sensoren quantitativ erfaßt werden unddaß Meßwerte aus den Sensoren nach einer Signalauswertung (SAW) für eine elektronische Bildstabilisierung des Sehfeldes am Boden verwendet werden, so daß aus dem über eine Mindestzeit ruhenden Bild die Erkennung eines Hubschraubers mittels der empfangenen Rotorblattfrequenz erfolgt. - Verfahren nach Anspruch 2, dadurch gekennzeichnet, daß das Bildfeld des Zielsuchkopfes nach erfolgter Zielerkennung durch kollineare Ausrichtung von Bildfeldachse und Flugkörperachse an das Ziel adaptiert wird.
- Verfahren nach Anspruch 2, dadurch gekennzeichnet, daß die Bildfeldadaption des Infrarot-Zielsuchkopfes beim Übergang von der Suchphase zur Zielverfolgungsphase durch einen optisch wirksamen Drehkeil (DK) erfolgt.
- 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.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19505791 | 1995-02-20 | ||
DE19505791A DE19505791C1 (de) | 1995-02-20 | 1995-02-20 | Verfahren und Vorrichtung zur Bekämpfung verdeckt operierender Hubschrauber |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0727638A1 EP0727638A1 (de) | 1996-08-21 |
EP0727638B1 true EP0727638B1 (de) | 2001-07-11 |
Family
ID=7754516
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP96102303A Expired - Lifetime EP0727638B1 (de) | 1995-02-20 | 1996-02-16 | Verfahren und Vorrichtung zur Bekämpfung verdeckt operierender Hubschrauber |
Country Status (3)
Country | Link |
---|---|
US (1) | US5874727A (de) |
EP (1) | EP0727638B1 (de) |
DE (2) | DE19505791C1 (de) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19610032C1 (de) * | 1996-03-14 | 1997-07-10 | Buck Chem Tech Werke | Verfahren zum Entdecken und Bekämpfen feindlicher Hubschrauber |
DE10001282C2 (de) | 2000-01-14 | 2001-10-25 | Lfk Gmbh | Verfahren zur autonomen Detektion von Hubschraubern |
DE10001519A1 (de) * | 2000-01-15 | 2017-11-02 | LFK Lenkflugkörpersysteme GmbH | Einrichtung zur Lenkung eines rollenden Flugkörpers |
FR2823295B1 (fr) * | 2001-04-10 | 2003-08-29 | Sagem | Perfectionnement au guidage terminal sur une cible d'une arme a imageur |
US7813644B2 (en) * | 2004-05-10 | 2010-10-12 | Raytheon Company | Optical device with a steerable light path |
DE102004037235A1 (de) * | 2004-07-31 | 2006-03-23 | Diehl Bgt Defence Gmbh & Co. Kg | Verfahren zum Schützen einer Immobilie gegen ein angreifendes Projektil |
US9127908B2 (en) * | 2009-02-02 | 2015-09-08 | Aero Vironment, Inc. | Multimode unmanned aerial vehicle |
CA3011940C (en) | 2009-09-09 | 2019-06-11 | Aerovironment, Inc. | Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable rf transparent launch tube |
EP3333776B1 (de) * | 2016-12-07 | 2021-01-27 | Porta Saber Lda | Aktivierung von rfid-transpondern mit licht |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4383663A (en) * | 1976-06-01 | 1983-05-17 | The United States Of America As Represented By The Secretary Of The Navy | Active optical terminal homing |
FR2686706A1 (fr) * | 1977-01-20 | 1993-07-30 | Telecommunications Sa | Procede et dispositif de detection infra-rouge d'un helicoptere en vol. |
DE2738507C3 (de) * | 1977-08-26 | 1980-08-07 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Verfahren zur Erhöhung der Treffwahrscheinlichkeit von gestörten Flugkörpern und Einrichtung zur Durchführung des Verfahrens |
DE2831825C2 (de) * | 1978-07-20 | 1986-05-07 | Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt | Zielanflugverfahren für einen sich selbst lenkenden Flugkörper |
FR2537263B2 (fr) * | 1981-06-04 | 1990-04-27 | Diehl Gmbh & Co | Dispositif destine a engendrer un signal d'amorcage pour missile de survol |
FR2517818A1 (fr) * | 1981-12-09 | 1983-06-10 | Thomson Brandt | Methode de guidage terminal et missile guide operant selon cette methode |
DE3334758A1 (de) * | 1983-09-26 | 1985-04-18 | Bundesrepublik Deutschland, vertreten durch den Bundesminister der Verteidigung, dieser vertreten durch den Präsidenten des Bundesamtes für Wehrtechnik und Beschaffung, 5400 Koblenz | Hubschrauberbekaempfungsverfahren mit lenkflugkoerper |
DE3733681C1 (de) * | 1987-10-05 | 1994-07-28 | Buck Chem Tech Werke | Vorrichtung mit Infrarot-Suchkopf zur Entdeckung und Bekämpfung feindlicher Hubschrauber |
DE3734758A1 (de) * | 1987-10-14 | 1989-05-03 | Messerschmitt Boelkow Blohm | Panzerabwehr-raketensystem |
DE3837842C1 (en) * | 1988-11-08 | 1990-05-10 | Eltro Gmbh, Gesellschaft Fuer Strahlungstechnik, 6900 Heidelberg, De | Method and sensor system for attacking helicopters |
DE3911576A1 (de) * | 1989-04-08 | 1990-10-11 | Rheinmetall Gmbh | Fluegelstabilisiertes geschoss |
-
1995
- 1995-02-20 DE DE19505791A patent/DE19505791C1/de not_active Expired - Fee Related
-
1996
- 1996-02-10 US US08/603,320 patent/US5874727A/en not_active Expired - Fee Related
- 1996-02-16 EP EP96102303A patent/EP0727638B1/de not_active Expired - Lifetime
- 1996-02-16 DE DE59607243T patent/DE59607243D1/de not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP0727638A1 (de) | 1996-08-21 |
DE59607243D1 (de) | 2001-08-16 |
DE19505791C1 (de) | 1996-08-14 |
US5874727A (en) | 1999-02-23 |
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