EP0580047B1 - Procédé pour le déclenchement du détonateur d'une tête militaire et dispositif pour la mise en oeuvre du procédé - Google Patents

Procédé pour le déclenchement du détonateur d'une tête militaire et dispositif pour la mise en oeuvre du procédé Download PDF

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Publication number
EP0580047B1
EP0580047B1 EP93111085A EP93111085A EP0580047B1 EP 0580047 B1 EP0580047 B1 EP 0580047B1 EP 93111085 A EP93111085 A EP 93111085A EP 93111085 A EP93111085 A EP 93111085A EP 0580047 B1 EP0580047 B1 EP 0580047B1
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EP
European Patent Office
Prior art keywords
filter bank
projectile
warhead
enemy
target
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
Application number
EP93111085A
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German (de)
English (en)
Other versions
EP0580047A1 (fr
Inventor
Anton Dipl.-Phys. Manhalter
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.)
Airbus Defence and Space GmbH
Original Assignee
Daimler Benz Aerospace AG
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Filing date
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Publication of EP0580047A1 publication Critical patent/EP0580047A1/fr
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Classifications

    • 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 according to the preamble of claim 6.
  • Such an arrangement is already known from GB-A-2 042 694.
  • the above-mentioned method and the associated arrangement are used, for example, to combat flight 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 described in GB-A-2 042 694 contains, for example, an active radar target seeker 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 in the active radar target seeker by means of distance measurement using a range-filter bank, and signals are 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 is reached, 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 enemy missile and the position of the warhead in the enemy 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 target, 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 transmit / receive 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 transmit / receive 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 enemy 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.
  • 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)

Claims (10)

  1. Procédé pour le déclenchement de l'amorçage d'une tête de frappe militaire (2), qui est une partie constitutive d'un corps volant (1) susceptible d'être dirigé pour le combat contre la tête de frappe militaire (12) d'un corps volant (11) ennemi arrivant en volant, et qui comprend une tête chercheuse de cible de radar active comportant une antenne (8) d'émission/de réception et une unité (6) d'évaluation et de commande, dans la tête chercheuse de cible de radar active, la position du corps volant (11) ennemi étant détectée par mesure d'éloignement et des signaux étant dérivés de celle-ci, grâce auxquels le corps volant (1) possédé, durant la phase de poursuite de cible et la phase d'approche de cible, est conduit vers le corps volant (11) ennemi, et, lors d'atteinte du corps volant (11) ennemi, l'amorçage de la tête de frappe militaire (2) du corps volant (1) possédé étant déclenché, caractérisé en ce que
    - lors d'approche de la tête de frappe militaire (2) du corps volant (1) possédé, durant la phase d'approche de cible au corps volant (11) ennemi, la tête chercheuse de cible de radar active sera commutée sur une discrimination fine d'éloignement au moyen d'un banc de filtrage de mesure d'éloignement à porte (9), un signal modulé supplémentaire étant émis par l'intermédiaire de l'antenne (8) d'émission/de réception de la tête chercheuse de cible de radar active, et, après réflexion, étant reçu au corps volant (11) ennemi ;
    - dans l'unité (6) d'évaluation et de commande de la tête chercheuse de cible de radar active, avec l'aide du signal reçu, une représentation imagée du corps volant (11) ennemi sera créée, et, la position de la tête de frappe militaire (12) dans le corps volant (11) ennemi, de façon préférée, sera estimée ou déterminée par comparaison avec des données sorties de mémoire ;
    - la tête de frappe militaire (2) du corps volant (1) possédé, consécutivement, sera conduite à la tête de frappe militaire (12) du corps volant (11) ennemi et sera amenée à l'explosion.
  2. Procédé selon la revendication 1, caractérisé en ce que, comme signal modulé supplémentaire, un signal modulé en fréquence, de façon préférée un signal modulé en fréquence avec changement de fréquence linéaire, sera choisi.
  3. Procédé selon une des précédentes revendications, caractérisé en ce que la représentation imagée du corps volant (11) ennemi, durant la phase de poursuite de cible, sera créée avec l'aide d'un premier banc de filtrage (51) pour la discrimination grossière d'éloignement, et, durant la phase d'approche de cible, sera créée avec l'aide du premier banc de filtrage (51) et d'un deuxième banc de filtrage (52) suivant pour la discrimination fine d'éloignement, les premier et deuxième bancs de filtrage (51, 52) étant des parties constitutives du banc de filtrage de mesure d'éloignement à porte (9).
  4. Procédé selon la revendication 3, caractérisé en ce que, lors du passage de la phase de poursuite de cible dans la phase d'approche de cible, les premier et deuxième bancs de filtrage (51, 52) seront déconnectés.
  5. Procédé selon la revendication 4, caractérisé en ce que, par l'intermédiaire de l'antenne (8) d'émission/de réception de la tête chercheuse de cible de radar, des signaux pulsés seront émis pour la discrimination grossière d'éloignement, et en ce que, durant la phase d'approche de cible, le signal modulé en fréquence sera superposé au signal pulsé.
  6. Agencement pour la mise en oeuvre du procédé selon une des précédentes revendications, lors duquel, le corps volant (1) possédé comporte une tête chercheuse de cible de radar active comprenant : une antenne (8) d'émission/de réception, une partie HF (3), un oscillateur (4), un banc de filtrage de mesure d'éloignement à porte (9) et une unité (6) d'évaluation et de commande, caractérisé en ce que le banc de filtrage de mesure d'éloignement à porte (9) consiste en : un premier banc de filtrage (51) pour la discrimination grossière d'éloignement, un deuxième banc de filtrage (52) pour la discrimination fine d'éloignement, un premier commutateur (71) et un deuxième commutateur (72), ainsi qu'en une branche de pontage (53) pontant le deuxième banc de filtrage (52), que le premier commutateur (71) du deuxième banc de filtrage (52) est mis en circuit devant celui-ci et le deuxième commutateur (72) est mis en circuit après celui-ci, et en ce que, chaque fois, suivant la position de commutation des deux commutateurs (71, 72), le deuxième banc de filtrage (52), ou la branche de pontage (53), sont déconnectés.
  7. Agencement selon la revendication 6, caractérisé en ce que l'antenne (8) d'émission/de réception, la partie HF (3), le banc de filtrage de mesure d'éloignement à porte (9) et l'unité (6) d'évaluation et de commande sont mis en circuit en série.
  8. Agencement selon une des revendications 6 ou 7, caractérisé en ce que le premier banc de filtrage (51) présente une largeur entre à peu près 2 à 200 m, de façon préférée entre à peu près 10 à 100 m, et/ou le deuxième banc de filtrage (52) présente une largeur entre à peu près 0 à 2 m, de façon préférée entre à peu près 25 à 100 cm.
  9. Agencement selon une des revendications 6 à 8, caractérisé en ce que l'oscillateur (4) est mis en circuit sur la partie HF (3) et travaille dans l'exploitation pulsée, et en ce qu'au signal pulsé de l'oscillateur (4), un signal modulé en fréquence, pour la discrimination fine d'éloignement, est superposé.
  10. Agencement selon une des précédentes revendications 6 à 9, caractérisé en ce que l'unité (6) d'évaluation et de commande commande le fonctionnement de l'oscillateur (4), ainsi que des premier et deuxième commutateurs (71, 72).
EP93111085A 1992-07-22 1993-07-10 Procédé pour le déclenchement du détonateur d'une tête militaire et dispositif pour la mise en oeuvre du procédé Expired - Lifetime EP0580047B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4224020 1992-07-22
DE4224020A DE4224020A1 (de) 1992-07-22 1992-07-22 Verfahren zur Auslösung der Zündung eines Gefechtskopfes und Anordnung zum Durchführen des Verfahrens

Publications (2)

Publication Number Publication Date
EP0580047A1 EP0580047A1 (fr) 1994-01-26
EP0580047B1 true EP0580047B1 (fr) 1996-09-25

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EP93111085A Expired - Lifetime EP0580047B1 (fr) 1992-07-22 1993-07-10 Procédé pour le déclenchement du détonateur d'une tête militaire et dispositif pour la mise en oeuvre du procédé

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Country Link
US (1) US5366179A (fr)
EP (1) EP0580047B1 (fr)
DE (2) DE4224020A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103471464A (zh) * 2013-09-29 2013-12-25 哈尔滨工业大学 无人机多路输出火控板及其通道设定方法和火箭发射方法

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Publication number Priority date Publication date Assignee Title
GB8626287D0 (en) * 1986-11-04 1986-12-03 Ucb Sa Substituted 1h-imidazoles
US5696347A (en) * 1995-07-06 1997-12-09 Raytheon Company Missile fuzing system
FR2770637B1 (fr) * 1997-11-03 1999-12-03 Giat Ind Sa Projectile a charge formee et systeme d'arme tirant un tel projectile
US6298787B1 (en) 1999-10-05 2001-10-09 Southwest Research Institute Non-lethal kinetic energy weapon system and method

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US3081050A (en) * 1954-04-27 1963-03-12 Bendix Corp Seeker system
US4227195A (en) * 1963-09-19 1980-10-07 The United States Of America As Represented By The Secretary Of The Army Fuze
US3858207A (en) * 1966-09-29 1974-12-31 Us Navy Range sensing target detecting device
US4360812A (en) * 1967-03-16 1982-11-23 The United States Of America As Represented By The Secretary Of The Army FM-CW Fuze
US4096480A (en) * 1968-06-10 1978-06-20 The United States Of America As Represented By The Secretary Of The Army Air target fuze time-gated decision circuit
FR2043871A5 (fr) * 1969-02-28 1971-02-19 Dassault Electronique
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
GB2042694A (en) * 1978-06-29 1980-09-24 Short Bros Ltd Fuzes for Guided Missiles
US4236157A (en) * 1978-12-22 1980-11-25 The United States Of America As Represented By The Secretary Of The Navy Target detection device
FR2468920A1 (fr) * 1979-10-26 1981-05-08 Thomson Csf Radar aeroporte a modulation de frequence et son application a un autodirecteur de missile
US4599616A (en) * 1983-07-05 1986-07-08 The United States Of America As Represented By The Secretary Of The Air Force Radar fuze system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103471464A (zh) * 2013-09-29 2013-12-25 哈尔滨工业大学 无人机多路输出火控板及其通道设定方法和火箭发射方法
CN103471464B (zh) * 2013-09-29 2015-05-13 哈尔滨工业大学 无人机多路输出火控板的通道设定方法

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Publication number Publication date
EP0580047A1 (fr) 1994-01-26
DE4224020A1 (de) 1994-01-27
DE59303945D1 (de) 1996-10-31
US5366179A (en) 1994-11-22

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