EP0580047A1 - Method for releasing an igniter of a warhead and apparatus for carrying out the method - Google Patents

Method for releasing an igniter of a warhead and apparatus for carrying out the method Download PDF

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Publication number
EP0580047A1
EP0580047A1 EP93111085A EP93111085A EP0580047A1 EP 0580047 A1 EP0580047 A1 EP 0580047A1 EP 93111085 A EP93111085 A EP 93111085A EP 93111085 A EP93111085 A EP 93111085A EP 0580047 A1 EP0580047 A1 EP 0580047A1
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EP
European Patent Office
Prior art keywords
missile
filter bank
warhead
active radar
target
Prior art date
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Granted
Application number
EP93111085A
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German (de)
French (fr)
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EP0580047B1 (en
Inventor
Anton Dipl.-Phys. Manhalter
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Airbus Defence and Space GmbH
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Deutsche Aerospace AG
Daimler Benz Aerospace AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/04—Proximity fuzes; Fuzes for remote detonation operated by radio waves
    • F42C13/045—Proximity fuzes; Fuzes for remote detonation operated by radio waves using transmission of F.M. waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/04—Proximity fuzes; Fuzes for remote detonation operated by radio waves
    • F42C13/042—Proximity fuzes; Fuzes for remote detonation operated by radio waves based on distance determination by coded radar techniques

Definitions

  • the invention relates to a method for triggering the ignition of a warhead according to the preamble of claim 1 and an arrangement for performing the method.
  • the above-mentioned method and the associated arrangement are used, for example, to combat targets and are preferably used in the field of missile defense.
  • the warhead to combat the warhead of an approaching enemy missile is part of a steerable missile.
  • the steerable missile contains an active radar seeker head Transmitting / receiving antenna and evaluation and control unit, which are connected to one another via a high-frequency part with an integrated oscillator, the position of the opposing missile being detected by distance measurement in the active radar seeker head and signals being derived therefrom by which the own missile during the target tracking and Target approach phase is directed to the enemy missile and when the enemy missile reaches the warhead of its own missile is triggered.
  • the destruction of the warhead of the opponent's missile in the air i.e. before reaching the ground target, is of the utmost importance in order to avoid damage to the ground target that could be caused by the opponent's missile to keep low.
  • Defense missiles with homing heads must therefore recognize the opposing missile from a great distance and steer as close as possible to its warhead.
  • An active target seeker can measure the distance to the opposing missile and thus in principle calculate the optimal ignition location and the associated optimal ignition timing. The currently achievable distance measurement accuracy is in the decimeter range.
  • the object of the invention is, on the one hand, to provide a method of the type mentioned at the outset, with which the position of the warhead of an enemy missile can be determined as precisely as possible, and, on the other hand, to provide an arrangement for carrying out such a method which is as simple as possible in construction is.
  • the solution to the problem in relation to the method is that when the warhead of one's own missile approaches the enemy missile during the target approach phase, the active radar target head is switched to anti-range discrimination by means of a range gate filter bank, with an additional modulated signal via the Transmitting / receiving antenna of the active radar seeker head is transmitted and received after reflection on the opposing missile and that in the evaluation and the control unit of the active radar target seeker uses the received signal to create an image of the opposing missile and the position of the warhead in the opposing missile is preferably estimated or determined by comparison with stored data.
  • the warhead of your own missile is then brought up to the warhead of the opposing missile and detonated.
  • the solution to the problem is that the own missile contains an active radar target seeker with a transmitting / receiving antenna, an HF part, an oscillator, a range filter bank and an evaluation and control unit.
  • a major advantage of the invention over previous solutions is that enemy missiles can be combated very effectively before they reach their destination, by the warhead of their own defense missile being close to it while the enemy missile is approaching, i.e. far from its target of the warhead of the enemy missile is directed and detonated there.
  • the own missile 1 contains an active radar target seeker with a transmitting / receiving antenna 8, an HF part 3 (HF stands for high frequency), an oscillator 4, a range filter bank 9 and an evaluation and control unit 6.
  • the transmitting / receiving antenna 8, the RF part 3, the distance gate filter bank 9 and the evaluation and control unit 6 are connected in series.
  • the distance gate filter bank 9 consists of a first filter bank 51 for gross distance discrimination, a second filter bank 52 for distance discrimination, a first and second changeover switch 71, 72 and a bridging branch 53 bridging the second filter bank 52, the first changeover switch 71 advancing the second filter bank 52.
  • the first filter bank 51 has, for example, a width between approximately 2 to 200 meters, preferably between approximately 10 to 100 meters
  • the second filter bank 52 has, for example, a width between approximately 0 to 2 meters, preferably between approximately 25 to 100 centimeters on.
  • the oscillator 4 is connected to the HF part 3. It works in pulse mode. The pulse signal of the oscillator 4 is during the target approach phase additionally a frequency-modulated signal for distance discrimination is superimposed.
  • the evaluation and control unit 6 controls the oscillator 4 and the first and the second changeover switch 71, 72.
  • the active radar seeker head is switched over to range-finding discrimination by means of a range-gate filter bank 9, an additional modulated signal being transmitted via the transmit / receive antenna 8 of the active radar Target seeker sent out and received after reflection on the opposing missile 11.
  • an image of the enemy missile 11 is created with the aid of the received signal and the position of the warhead 12 in the enemy missile 11 is e.g. estimated or determined by comparison with stored data.
  • the warhead 2 of its own missile 1 is subsequently, i.e. brought to the warhead of the enemy missile in the final control phase and detonated there.
  • a frequency-modulated signal preferably a frequency-modulated signal with a linear frequency change, is selected as an additional modulated signal.
  • the pulse signals of the oscillator 4 for gross range discrimination are emitted via the transmit / receive antenna 8 of the active radar seeker head, reflected on the opposing missile and received again by the transmit / receive antenna 8.
  • the frequency-modulated signal is superimposed on the pulse signal.
  • the image of the opposing missile 11 results - during the target tracking phase with the aid of the first filter bank 51 for gross range discrimination and during the target approach phase with the aid of the first filter bank 51 and the following second filter bank 52 for range discrimination - from the filtering of the received echo signals in the range gate filter bank .
  • the first and second filter banks 51, 52 are activated for this purpose.
  • an image of the opposing missile 11 is also generated in the evaluation and control unit 6, which is created by selecting echo signals in the target search phase and tracking phase in the first filter 51. If the resulting function is plotted as a probability distribution of the distance measurement error as a function of the offset ⁇ R from the center of an ideally tracking distance gate (first filter), a continuous function is created in front of the first filter bank 51 (FIG. 1) as shown in FIG. 2 shown in dashed lines is. The spades shown in the figure arise at the outlet of the first filter bank 51.
  • an additional modulated signal is emitted and the echo signal is selected approximately simultaneously, on the one hand by means of the first filter bank 51 and on the other hand by means of an activated second filter bank 52 (see FIG. 1).
  • the distances between the spades are smaller and the contour of the opposing missile 11 is sharper.
  • the invention is not limited to the exemplary embodiments shown, but rather can be transferred to others.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

When one's own missile (1) approaches the enemy missile during the target approach phase (terminal homing phase), the active radar homing head (2) is switched to fine range discrimination (52), an additional modulated signal being transmitted via the transmitting/receiving antenna (8) of the active radar homing head (2), and being received after reflection on the enemy missile. An image of the enemy missile is created in the evaluation and control unit (6) of the active radar homing head (2), with the aid of the received signal, and the position of the warhead in the enemy missile is determined. The warhead of one's own missile (1) is subsequently guided to the warhead of the enemy missile and is caused to explode there. One's own missile contains an active radar homing head (2) having a transmitting/receiving antenna (8), an RF section (3), an oscillator (4), a range-gate filter bank (9) and an evaluation and control unit (6). <IMAGE>

Description

Die Erfindung betrifft ein Verfahren zur Auslösung der Zündung eines Gefechtskopfes gemäß Oberbegriff des Patentanspruchs 1 sowie eine Anordnung zum Durchführen des Verfahrens.The invention relates to a method for triggering the ignition of a warhead according to the preamble of claim 1 and an arrangement for performing the method.

Das oben genannte Verfahren und die zugehörige Anordnung werden beispielsweise zur Flugzielbekämpfung eingesetzt und kommen bevorzugt im Bereich der Flugkörperabwehr zur Anwendung. Der Gefechtskopf zur Bekämpfung des Gefechtskopfes eines anfliegenden gegnerischen Flugkörpers ist dabei Bestandteil eines lenkbaren Flugkörpers. Der lenkbare Flugkörper enthält einen aktiven Radar-Zielsuchkopf mit Sende/Empfangsantenne und Auswerte- und Steuereinheit, die miteinander über ein Hochfrequenzteil mit integriertem Oszillator verbunden sind, wobei im aktiven Radar-Zielsuchkopf die Position des gegnerischen Flugkörpers durch Entfernungsmessung erfaßt und daraus Signale abgeleitet werden, durch die der eigene Flugkörper während der Zielverfolgungs- und Zielannäherungsphase zu dem gegnerischen Flugkörper hingeführt wird und bei Erreichen des gegnerischen Flugkörpers die Zündung des Gefechtskopfes des eigenen Flugkörpers ausgelöst wird.The above-mentioned method and the associated arrangement are used, for example, to combat targets and are preferably used in the field of missile defense. The warhead to combat the warhead of an approaching enemy missile is part of a steerable missile. The steerable missile contains an active radar seeker head Transmitting / receiving antenna and evaluation and control unit, which are connected to one another via a high-frequency part with an integrated oscillator, the position of the opposing missile being detected by distance measurement in the active radar seeker head and signals being derived therefrom by which the own missile during the target tracking and Target approach phase is directed to the enemy missile and when the enemy missile reaches the warhead of its own missile is triggered.

Befindet sich der gegnerische Flugkörper z.B. im Sturzflug auf ein Bodenziel, so ist der Zerstörung des Gefechtskopfes des gegnerischen Flugkörpers bereits in der Luft, d.h. vor Erreichen des Bodenziels größte Bedeutung beizumessen, um Schäden am Bodenziel, die durch den gegnerischen Flugkörper verursacht werden könnten, möglichst gering zu halten. Abwehrflugkörper mit Zielsuchköpfen müssen daher den gegnerischen Flugkörper bereits auf große Entfernung erkennen und sich so nahe wie möglich an dessen Gefechtskopf heranlenken. Ein aktiver Zielsuchkopf kann die Entfernung zum gegnerischen Flugkörper messen und somit prinzipiell den optimalen Zündort und damit verbunden den optimalen Zündzeitpunkt berechnen. Die derzeit erreichbare Entfernungsmeßgenauigkeit liegt hierbei im Dezimeterbereich. Alle bisher vorgeschlagenen Verfahren zur Lenkung von Flugkörpern liefern somit eine Entfernungsmeßgenauigkeit (vom Gefechtskopf des Abwehrflugkörpers zum Gefechtskopf des gegnerischen Flugkörpers), die um eine bis zwei Zehnerpotenzen über dem tolerierbaren Wert für den optimalen Zündzeitpunkt liegt. Diese Ungenauigkeit wird vor allem durch Interferenzen der einzelnen Streuzentren des angreifenden Flugkörpers verursacht. Die Interferenzen führen wegen ihres statistischen Charakters zu einem statistischen Entfernungsfehler, was die Bekämpfung des gegnerischen Flugkörpers drastisch erschwert.If the enemy missile is, for example, in a dive on a ground target, the destruction of the warhead of the opponent's missile in the air, i.e. before reaching the ground target, is of the utmost importance in order to avoid damage to the ground target that could be caused by the opponent's missile to keep low. Defense missiles with homing heads must therefore recognize the opposing missile from a great distance and steer as close as possible to its warhead. An active target seeker can measure the distance to the opposing missile and thus in principle calculate the optimal ignition location and the associated optimal ignition timing. The currently achievable distance measurement accuracy is in the decimeter range. All previously proposed methods for guiding missiles thus provide a range-of-measurement accuracy (from the warhead of the defensive missile to the warhead of the opposing missile) which is one to two powers of ten above the tolerable value for the optimum ignition timing. This inaccuracy is mainly due to interference from the causes individual scattering centers of the attacking missile. Because of their statistical nature, the interferences lead to a statistical range error, which makes it difficult to combat the enemy missile.

Die Aufgabe der Erfindung besteht darin, zum einen ein Verfahren der eingangs genannten Art anzugeben, mit dem die Position des Gefechtskopfes eines gegnerischen Flugkörpers möglichst genau bestimmt werden kann, und zum andern eine Anordnung zur Durchführung eines solchen Verfahrens zu schaffen, die möglichst einfach im Aufbau ist.The object of the invention is, on the one hand, to provide a method of the type mentioned at the outset, with which the position of the warhead of an enemy missile can be determined as precisely as possible, and, on the other hand, to provide an arrangement for carrying out such a method which is as simple as possible in construction is.

Diese Aufgabe wird in bezug auf das zu schaffende Verfahren durch die im kennzeichnenden Teil des Patentanspruchs 1 angegebenen Merkmale und in bezug auf die zu schaffende Anordnung durch die im kennzeichnenden Teil des Patentanspruchs 6 angegebenen Merkmale gelöst. Vorteilhafte Ausgestaltungen und/oder Weiterbildungen der Erfindung sind in den Ansprüchen 2 bis 5 bezüglich des zu realisierenden Verfahrens bzw. in den Ansprüchen 7 bis 11 bezüglich der zu schaffenden Anordnung beschrieben.This object is achieved in relation to the method to be created by the features specified in the characterizing part of patent claim 1 and in relation to the arrangement to be created by the features specified in the characterizing part of patent claim 6. Advantageous refinements and / or developments of the invention are described in claims 2 to 5 with respect to the method to be implemented and in claims 7 to 11 with respect to the arrangement to be created.

Die Lösung der Aufgabe besteht in Bezug auf das Verfahren darin, daß bei Annäherung des Gefechtskopfes des eigenen Flugkörpers während der Zielannäherungsphase an den gegnerischen Flugkörper der aktive Radar-Zielkopf auf eine Entfernungsfeindiskriminierung mittels einer Entfernungstor-Filterbank geschaltet wird, wobei ein zusätzliches moduliertes Signal über die Sende/Empfangsantenne des aktiven Radar-Zielsuchkopfes ausgesendet und nach Reflexion am gegnerischen Flugkörper empfangen wird und daß in der Auswerte- und Steuereinheit des aktiven Radar-Zielsuchkopfes mit Hilfe des empfangenen Signals ein Abbild des gegnerischen Flugkörpers geschaffen wird und die Position des Gefechtskopfes im gegnerischen Flugkörper vorzugsweise geschätzt oder durch Vergleich mit abgespeicherten Daten bestimmt wird.The solution to the problem in relation to the method is that when the warhead of one's own missile approaches the enemy missile during the target approach phase, the active radar target head is switched to anti-range discrimination by means of a range gate filter bank, with an additional modulated signal via the Transmitting / receiving antenna of the active radar seeker head is transmitted and received after reflection on the opposing missile and that in the evaluation and the control unit of the active radar target seeker uses the received signal to create an image of the opposing missile and the position of the warhead in the opposing missile is preferably estimated or determined by comparison with stored data.

Der Gefechtskopf des eigenen Flugkörpers wird anschließend an den Gefechtskopf des gegnerischen Flugkörpers herangeführt und zur Explosion gebracht.The warhead of your own missile is then brought up to the warhead of the opposing missile and detonated.

Bezüglich der zu schaffenden Anordnung besteht die Lösung der Aufgabe darin, daß der eigene Flugkörper einen aktiven Radar-Zielsuchkopf enthält mit einer Sende/Empfangsantenne, einem HF-Teil, einem Oszillator, einer Entfernungstor-Filterbank und einer Auswerte- und Steuereinheit.With regard to the arrangement to be created, the solution to the problem is that the own missile contains an active radar target seeker with a transmitting / receiving antenna, an HF part, an oscillator, a range filter bank and an evaluation and control unit.

Ein wesentlicher Vorteil der Erfindung gegenüber bisherigen Lösungen liegt darin, daß gegnerische Flugkörper sehr wirksam bekämpft werden können, bevor sie ihr Ziel erreichen, indem der Gefechtskopf des eigenen Abwehrflugkörpers noch während des Anfluges des gegnerischen Flugkörpers, also weit von dessen Ziel entfernt, in unmittelbare Nähe des Gefechtskopfes des gegnerischen Flugkörpers gelenkt und dort zur Explosion gebracht wird (werden kann).A major advantage of the invention over previous solutions is that enemy missiles can be combated very effectively before they reach their destination, by the warhead of their own defense missile being close to it while the enemy missile is approaching, i.e. far from its target of the warhead of the enemy missile is directed and detonated there.

Die Erfindung wird exemplarisch anhand der Figuren näher eräutert. Es zeigen:

FIG. 1
ein Längsschnittbild durch eine bevorzugte Ausführungsform des erfindungsgemäßen eigenen Flugkörpers im Ausschnitt;
FIG. 2
ein mit einer bevorzugten Ausführungsform des erfindungsgemäßen Verfahrens erzielbares Abbild eines möglichen gegnerischen Flugkörpers.
The invention is illustrated by way of example with reference to the figures. Show it:
FIG. 1
a longitudinal section through a preferred embodiment of the own missile according to the invention in the detail;
FIG. 2nd
an image of a possible enemy missile obtainable with a preferred embodiment of the method according to the invention.

Der eigene Flugkörper 1 nach FIG. 1 enthält einen aktiven Radar-Zielsuchkopf mit einer Sende/Empfangsantenne 8, einem HF-Teil 3 (HF steht für Hochfrequenz), einem Oszillator 4, einer Entfernungstor-Filterbank 9 und einer Auswerte- und Steuereinheit 6. Die Sende/Empfangsantenne 8, das HF-Teil 3, die Entfernungstor-Filterbank 9 und die Auswerte- und Steuereinheit 6 sind seriell verschaltet. Die Entfernungstor-Filterbank 9 besteht aus einer ersten Filterbank 51 zur Entfernungsgrobdiskriminierung, einer zweiten Filterbank 52 zur Entfernungsfeindiskriminierung, einem ersten und zweiten Umschalter 71, 72 sowie einem die zweite Filterbank 52 überbrückenden Überbrückungszweig 53, wobei der erste Umschalter 71 der zweiten Filterbank 52 vor- und der zweite Umschalter 72 dieser nachgeschaltet ist und je nach Schalterstellung der beiden Umschalter 71, 72 die zweite Filterbank 52 oder der Überbrückungszweig 53 freigeschaltet ist. Die erste Filterbank 51 weist beispielsweise eine Breite zwischen in etwa 2 bis 200 Meter, vorzugsweise zwischen in etwa 10 bis 100 Meter auf und die zweite Filterbank 52 weist beispielsweise eine Breite zwischen in etwa 0 bis 2 Meter, vorzugsweise zwischen in etwa 25 bis 100 Zentimeter auf. Der Oszillator 4 ist auf das HF-Teil 3 aufgeschaltet ist. Er arbeitet im Pulsbetrieb. Dem Pulssignal des Oszillators 4 ist während der Zielannäherungsphase zusätzlich ein frequenzmoduliertes Signal zur Entfernungsdiskriminierung überlagert. Die Auswerte- und Steuereinheit 6 steuert den Oszillator 4 sowie den ersten und den zweiten Umschalter 71, 72 an.The own missile 1 according to FIG. 1 contains an active radar target seeker with a transmitting / receiving antenna 8, an HF part 3 (HF stands for high frequency), an oscillator 4, a range filter bank 9 and an evaluation and control unit 6. The transmitting / receiving antenna 8, the RF part 3, the distance gate filter bank 9 and the evaluation and control unit 6 are connected in series. The distance gate filter bank 9 consists of a first filter bank 51 for gross distance discrimination, a second filter bank 52 for distance discrimination, a first and second changeover switch 71, 72 and a bridging branch 53 bridging the second filter bank 52, the first changeover switch 71 advancing the second filter bank 52. and the second changeover switch 72 is connected downstream thereof and, depending on the switch position of the two changeover switches 71, 72, the second filter bank 52 or the bridging branch 53 is activated. The first filter bank 51 has, for example, a width between approximately 2 to 200 meters, preferably between approximately 10 to 100 meters, and the second filter bank 52 has, for example, a width between approximately 0 to 2 meters, preferably between approximately 25 to 100 centimeters on. The oscillator 4 is connected to the HF part 3. It works in pulse mode. The pulse signal of the oscillator 4 is during the target approach phase additionally a frequency-modulated signal for distance discrimination is superimposed. The evaluation and control unit 6 controls the oscillator 4 and the first and the second changeover switch 71, 72.

Bei Annäherung des Gefechtskopfes 2 des eigenen Flugkörpers 1 während der Zielannäherungsphase an den gegnerischen Flugkörper 11 wird der aktive Radar-Zielsuchkopf auf eine Entfernungsfeindiskriminierung mittels einer Entfernungstor-Filterbank 9 umgeschaltet, wobei zusätzlich ein zusätzliches moduliertes Signal über die Sende/Empfangsantenne 8 des aktiven Radar-Zielsuchkopfes ausgesendet und nach Reflexion am gegnerischen Flugkörper 11 empfangen wird.When the warhead 2 of one's own missile 1 approaches the opposing missile 11 during the target approach phase, the active radar seeker head is switched over to range-finding discrimination by means of a range-gate filter bank 9, an additional modulated signal being transmitted via the transmit / receive antenna 8 of the active radar Target seeker sent out and received after reflection on the opposing missile 11.

In der Auswerte- und Steuereinheit 6 des aktiven Radar-Zielsuchkopfes werden mit Hilfe des empfangenen Signals ein Abbild des gegnerischen Flugkörpers 11 geschaffen und die Position des Gefechtskopfes 12 im gegnerischen Flugkörper 11 z.B. geschätzt oder durch Vergleich mit abgespeicherten Daten bestimmt.In the evaluation and control unit 6 of the active radar target seeker, an image of the enemy missile 11 is created with the aid of the received signal and the position of the warhead 12 in the enemy missile 11 is e.g. estimated or determined by comparison with stored data.

Der Gefechtskopf 2 des eigenen Flugkörpers 1 wird anschließend, d.h. in der Endlenkphase an den Gefechtskopf des gegnerischen Flugkörpers herangeführt und dort zur Explosion gebracht.The warhead 2 of its own missile 1 is subsequently, i.e. brought to the warhead of the enemy missile in the final control phase and detonated there.

Als zusätzliches moduliertes Signal wird ein frequenzmoduliertes Signal, vorzugsweise ein frequenzmoduliertes Signal mit linearer Frequenzänderung gewählt.A frequency-modulated signal, preferably a frequency-modulated signal with a linear frequency change, is selected as an additional modulated signal.

Über die Sende/Empfangsantenne 8 des aktiven Radar-Zielsuchkopfes werden die Pulssignale des Oszillators 4 zur Entfernungsgrobdiskriminierung ausgesendet, am gegnerischen Flugkörper reflektiert und von der Sende/Empfangsantenne 8 wieder empfangen. Während der Zielannäherungsphase wird das frequenzmodulierte Signal dem Pulssignal überlagert.The pulse signals of the oscillator 4 for gross range discrimination are emitted via the transmit / receive antenna 8 of the active radar seeker head, reflected on the opposing missile and received again by the transmit / receive antenna 8. During the target approach phase, the frequency-modulated signal is superimposed on the pulse signal.

Das Abbild des gegnerischen Flugkörpers 11 ergibt sich - während der Zielverfolgungsphase mit Hilfe der ersten Filterbank 51 zur Entfernungsgrobdiskriminierung und während der Zielannäherungsphase mit Hilfe der ersten Filterbank 51 und der folgenden zweiten Filterbank 52 zur Entfernungsfeindiskriminierung - aus der Filterung der empfangenen Echosignale in der Entfernungstor-Filterbank.The image of the opposing missile 11 results - during the target tracking phase with the aid of the first filter bank 51 for gross range discrimination and during the target approach phase with the aid of the first filter bank 51 and the following second filter bank 52 for range discrimination - from the filtering of the received echo signals in the range gate filter bank .

Beim Übergang von der Zielverfolgungsphase in die Zielannäherungsphase werden zu diesem Zweck die ersten und zweiten Filterbank 51, 52 freigeschaltet.During the transition from the target tracking phase to the target approach phase, the first and second filter banks 51, 52 are activated for this purpose.

Alternativ zum zuvor geschilderten Vergleich des Abbildes mit abgespeicherten Daten oder zur Schätzung kann, wie in FIG. 2 gezeigt, auch ein Abbild des gegnerischen Flugkörpers 11 in der Auswerte- und Steuereinheit 6 generiert werden, das dadurch entsteht, daß Echosignale in der Zielsuchphase und -Verfolgungsphase in dem ersten Filter 51 selektiert werden. Trägt man die hierbei entstehende Funktion als Wahrscheinlichkeitsverteilung des Entfernungsmeßfehlers als Funktion der Ablage ΔR aus der Mitte eines ideal verfolgenden Entfernungstors (erster Filter) auf, so entsteht vor der ersten Filterbank 51 (FIG. 1) eine stetige Funktion wie sie in FIG. 2 gestrichelt dargestellt ist. Am Ausgang der ersten Filterbank 51 entstehen die in der Figur dargestellten Piks. Während der Zielannäherungsphase erfolgt, wie oben beschrieben, die Aussendung eines zusätzlichen modulierten Signals und in etwa gleichzeitig eine Selektion des Echosignales zum einen mittels der ersten Filterbank 51 und zum anderen mittels einer zugeschalteten zweiten Filterbank 52 (siehe FIG. 1). Hierdurch werden die Abstände der Piks zueinander kleiner und die Kontur des gegnerischen Flugkörpers 11 schärfer.As an alternative to the previously described comparison of the image with stored data or for estimation, as shown in FIG. 2, an image of the opposing missile 11 is also generated in the evaluation and control unit 6, which is created by selecting echo signals in the target search phase and tracking phase in the first filter 51. If the resulting function is plotted as a probability distribution of the distance measurement error as a function of the offset ΔR from the center of an ideally tracking distance gate (first filter), a continuous function is created in front of the first filter bank 51 (FIG. 1) as shown in FIG. 2 shown in dashed lines is. The spades shown in the figure arise at the outlet of the first filter bank 51. During the target approach phase, as described above, an additional modulated signal is emitted and the echo signal is selected approximately simultaneously, on the one hand by means of the first filter bank 51 and on the other hand by means of an activated second filter bank 52 (see FIG. 1). As a result, the distances between the spades are smaller and the contour of the opposing missile 11 is sharper.

Die Erfindung ist nicht auf die dargestellten Ausführungsbeispiele beschränkt, sondern vielmehr auf weitere übertragbar.The invention is not limited to the exemplary embodiments shown, but rather can be transferred to others.

So ist es z.B. möglich, anstelle von Pulssignalen zur Entfernungsgrobdiskriminierung CW-Signale zu verwenden.So it is e.g. possible to use CW signals instead of pulse signals for gross range discrimination.

Claims (11)

Verfahren zur Auslösung der Zündung eines Gefechtskopfes, der Bestandteil eines lenkbaren Flugkörpers zur Bekämpfung des Gefechtskopfes eines anfliegenden gegnerischen Flugkörpers ist und der einen aktiven Radar-Zielsuchkopf mit Sende/Empfangsantenne und Auswerte- und Steuereinheit enthält, wobei im aktiven Radar-Zielsuchkopf die Position des gegnerischen Flugkörpers durch Entfernungsmessung erfaßt und daraus Signale abgeleitet werden, durch die der eigene Flugkörper während der Zielverfolgungs- und Zielannäherungsphase zu dem gegnerischen Flugkörper hingeführt wird und bei Erreichen des gegnerischen Flugkörpers die Zündung des Gefechtskopfes des eigenen Flugkörpers ausgelöst wird, dadurch gekennzeichnet, daß - bei Annäherung des Gefechtskopfes (2) des eigenen Flugkörpers (1) während der Zielannäherungsphase an den gegnerischen Flugkörper (11) der aktive Radar-Zielsuchkopf auf eine Entfernungsfeindiskriminierung mittels einer Entfernungstor-Filterbank (9) umgeschaltet wird, wobei ein zusätzliches moduliertes Signal über die Sende/Empfangsantenne (8) des aktiven Radar-Zielsuchkopfes ausgesendet und nach Reflexion am gegnerischen Flugkörper (11) empfangen wird; - in der Auswerte- und Steuereinheit (6) des aktiven Radar-Zielsuchkopfes mit Hilfe des empfangenen Signals ein Abbild des gegnerischen Flugkörpers (11) geschaffen wird und die Position des Gefechtskopfes (12) im gegnerischen Flugkörper (11) vorzugsweise geschätzt oder durch Vergleich mit abgespeicherten Daten bestimmt wird; - der Gefechtskopf (2) des eigenen Flugkörpers (1) anschließend an den Gefechtskopf (12) des gegnerischen Flugkörpers (11) herangeführt wird und zur Explosion gebracht wird. Process for triggering the ignition of a warhead, which is part of a steerable missile for combating the warhead of an approaching enemy missile and which contains an active radar seeker head with transmitting / receiving antenna and evaluation and control unit, the position of the opposing one in the active radar seeker head Missile detected by distance measurement and signals derived therefrom, through which the own missile is guided to the opposing missile during the target tracking and target approach phase and when the opposing missile reaches the warhead of the own missile is triggered, characterized in that - When the warhead (2) of one's own missile (1) approaches the opposing missile (11) during the target approach phase, the active radar target seeker is switched to anti-range discrimination by means of a range gate filter bank (9), with an additional modulated signal via the Transmitting / receiving antenna (8) of the active radar seeker is transmitted and received after reflection on the opposing missile (11); - In the evaluation and control unit (6) of the active radar target seeker with the help of the received signal, an image of the enemy missile (11) is created and the position of the warhead (12) in the enemy missile (11) is preferably estimated or by comparison with stored data is determined; - The warhead (2) of its own missile (1) is then brought up to the warhead (12) of the opposing missile (11) and is brought to an explosion. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß als zusätzliches moduliertes Signal ein frequenzmoduliertes Signal, vorzugsweise ein frequenzmoduliertes Signal mit linearer Frequenzänderung gewählt wird.Method according to Claim 1, characterized in that a frequency-modulated signal, preferably a frequency-modulated signal with a linear frequency change, is selected as the additional modulated signal. Verfahren nach einem der vorherigen Ansprüche, dadurch gekennzeichnet, daß das Abbild des gegnerischen Flugkörpers (11) während der Zielverfolgungsphase mit Hilfe einer ersten Filterbank (51) zur Entfernungsgrobdiskriminierung und während der Zielannäherungsphase mit Hilfe der ersten Filterbank (51) und einer folgenden zweiten Filterbank (52) zur Entfernungsfeindiskriminierung geschaffen wird, wobei die erste und zweite Filterbank (51, 52) Bestandteil der Entfernungstor-Filterbank (9) sind.Method according to one of the preceding claims, characterized in that the image of the opposing missile (11) during the target tracking phase with the aid of a a first filter bank (51) for gross range discrimination and during the target approach phase with the aid of the first filter bank (51) and a following second filter bank (52) for distance discrimination, the first and second filter banks (51, 52) being part of the range gate filter bank (9 ) are. Verfahren nach Anspruch 3, dadurch gekennzeichnet, daß beim Übergang von der Zielverfolgungsphase in die Zielannäherungsphase die erste und die zweite Filterbank (51, 52) freigeschaltet werden.Method according to Claim 3, characterized in that the first and second filter banks (51, 52) are activated during the transition from the target tracking phase to the target approach phase. Verfahren nach Anspruch 4, dadurch gekennzeichnet, daß über die Sende/Empfangsantenne (8) des aktiven Radar-Zielsuchkopfes Pulssignale zur Entfernungsgrobdiskriminierung ausgesendet werden und daß während der Zielannäherungsphase das frequenzmodulierte Signal dem Pulssignal überlagert wird.Method according to Claim 4, characterized in that pulse signals for gross range discrimination are emitted via the transmitting / receiving antenna (8) of the active radar target seeker and that the frequency-modulated signal is superimposed on the pulse signal during the target approach phase. Anordnung zur Durchführung des Verfahrens nach einem der vorherigen Ansprüche, dadurch gekennzeichnet, daß der eigene Flugkörper (1) einen aktiven Radar-Zielsuchkopf enthält mit einer Sende/Empfangsantenne (8), einem HF-Teil (3), einem Oszillator (4), einer Entfernungstor-Filterbank (9) und einer Auswerte- und Steuereinheit (6).Arrangement for carrying out the method according to one of the preceding claims, characterized in that the own missile (1) contains an active radar target seeker with a transmitting / receiving antenna (8), an HF part (3), an oscillator (4), a distance gate filter bank (9) and an evaluation and control unit (6). Anordnung nach Anspruch 6, dadurch gekennzeichnet, daß die Sende/Empfangsantenne (8), das HF-Teil (3), die Entfernungstor-Filterbank (9) und die Auswerte- und Steuereinheit (6) seriell verschaltet sind.Arrangement according to claim 6, characterized in that the transmitting / receiving antenna (8), the HF part (3), the range gate filter bank (9) and the evaluation and control unit (6) are connected in series. Anordnung nach einem der Ansprüche 6 oder 7, dadurch gekennzeichnet, daß die Entfernungstor-Filterbank (9) aus einer ersten Filterbank (51) zur Entfernungsgrobdiskriminierung, einer zweiten Filterbank (52) zur Entfernungsfeindiskriminierung, einem ersten und zweiten Umschalter (71, 72) sowie einem die zweite Filterbank (52) überbrückenden Überbrückungszweig (53) besteht, daß der erste Umschalter (71) der zweiten Filterbank (52) vor- und der zweite Umschalter (72) dieser nachgeschaltet ist und daß je nach Schalterstellung der beiden Umschalter (71, 72) die zweite Filterbank (52) oder der Überbrückungszweig (53) freigeschaltet ist.Arrangement according to one of claims 6 or 7, characterized in that the distance gate filter bank (9) consists of a first filter bank (51) for gross distance discrimination, a second filter bank (52) for distance discrimination, a first and second switch (71, 72) and In a bridging branch (53) bridging the second filter bank (52), the first changeover switch (71) is connected upstream of the second filter bank (52) and the second changeover switch (72) is connected downstream thereof, and depending on the switch position of the two changeover switches (71, 72) the second filter bank (52) or the bridging branch (53) is activated. Anordnung nach Anspruch 8, dadurch gekennzeichnet, daß die erste Filterbank (51) eine Breite zwischen in etwa 2 bis 200 Meter, vorzugsweise zwischen in etwa 10 bis 100 Meter aufweist und/oder die zweite Filterbank (52) eine Breite zwischen in etwa 0 bis 2 Meter, vorzugsweise zwischen in etwa 25 bis 100 Zentimeter aufweist.Arrangement according to claim 8, characterized in that the first filter bank (51) has a width between approximately 2 to 200 meters, preferably between approximately 10 to 100 meters and / or the second filter bank (52) has a width between approximately 0 to 2 meters, preferably between about 25 to 100 centimeters. Anordnung nach einem der Ansprüche 6 bis 9, dadurch gekennzeichnet, daß der Oszillator (4) auf das HF-Teil (3) aufgeschaltet ist und im Pulsbetrieb arbeitet und daß dem Pulssignal des Oszillators (4) ein frequenzmoduliertes Signal zur Entfernungsfeindiskriminierung überlagert ist.Arrangement according to one of claims 6 to 9, characterized in that the oscillator (4) is connected to the HF part (3) and operates in pulse mode and that a frequency-modulated signal for distance discrimination is superimposed on the pulse signal of the oscillator (4). Anordnung nach einem der vorherigen Ansprüche 6 bis 10, dadurch gekennzeichnet, daß die Auswerte- und Steuereinheit (6) den Oszillator (4) sowie den ersten und den zweiten Umschalter (71, 72) ansteuert.Arrangement according to one of the preceding claims 6 to 10, characterized in that the evaluation and control unit (6) controls the oscillator (4) and the first and the second changeover switch (71, 72).
EP93111085A 1992-07-22 1993-07-10 Method for releasing an igniter of a warhead and apparatus for carrying out the method Expired - Lifetime EP0580047B1 (en)

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DE4224020 1992-07-22
DE4224020A DE4224020A1 (en) 1992-07-22 1992-07-22 Method for triggering the warhead and arrangement for carrying out the method

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DE4224020A1 (en) 1994-01-27
EP0580047B1 (en) 1996-09-25
US5366179A (en) 1994-11-22

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