EP0137910A1 - Projectile head to be launched by a carrier projectile or missile - Google Patents

Projectile head to be launched by a carrier projectile or missile Download PDF

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Publication number
EP0137910A1
EP0137910A1 EP84106683A EP84106683A EP0137910A1 EP 0137910 A1 EP0137910 A1 EP 0137910A1 EP 84106683 A EP84106683 A EP 84106683A EP 84106683 A EP84106683 A EP 84106683A EP 0137910 A1 EP0137910 A1 EP 0137910A1
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EP
European Patent Office
Prior art keywords
antenna
projectile
projectile head
target
head according
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.)
Granted
Application number
EP84106683A
Other languages
German (de)
French (fr)
Other versions
EP0137910B1 (en
Inventor
Wolfram Dr. Witt
Hendrik Lips
Herbert Dr. Scholles
Raimund Schweiger
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Rheinmetall Industrie AG
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Rheinmetall GmbH
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Publication date
Application filed by Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0137910A1 publication Critical patent/EP0137910A1/en
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Publication of EP0137910B1 publication Critical patent/EP0137910B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G9/00—Systems for controlling missiles or projectiles, not provided for elsewhere
    • F41G9/02—Systems for controlling missiles or projectiles, not provided for elsewhere for bombing control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/006—Mounting of sensors, antennas or target trackers on projectiles
    • 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
    • F42C13/006—Proximity fuzes; Fuzes for remote detonation for non-guided, spinning, braked or gravity-driven weapons, e.g. parachute-braked sub-munitions

Definitions

  • the invention relates to a projectile head that can be ejected from a cargo projectile or missile.
  • the projectile heads of the generic type are ejected from a cargo floor or missile and then sink over a target area, braked by a parachute, whereby they independently a target, for. B. an armored vehicle, capture and combat it after reaching the combat range.
  • a detachable projectile head which has an ignitable charge to combat the target, which hurls a secondary projectile onto the recognized target.
  • the secondary storey is formed from a flat charge that is deformed in the direction of flight before ignition to the secondary storey.
  • the detachable projectile head has a target recognition device with a transmitter, a receiver and an antenna for target acquisition.
  • the target location device including the antenna and additional guide surfaces are arranged in the direction of flight in front of the flat charge.
  • the invention has for its object to provide a projectile from a cargo floor or missile projectile head that is able to a secondary floor with max. Generate reach and penetration.
  • a charge 15, a flat coating 16 ′ arranged thereon to form a secondary projectile 16, a target recognition device 14 and a detonator 13 for activating the charge 15 are arranged within the casing 9 of the projectile head 10 according to FIG. 1.
  • the connecting lines between the projectile head 10 and the case screen 12 are designated by reference number 11.
  • FIG. 2 shows a partial section of the projectile head 10 with the flat occupancy 16 ′ arranged in the front in the flight direction, which is converted by a charge 15 activated by an igniter 13 after detection of a target and reaching the control range to a secondary projectile 16 destroying the target.
  • the igniter 13 in turn is connected via an ignition line 13 'to the target recognition device 14, which is arranged in the direction of flight behind the flat occupancy 16' and the charge 15.
  • the target recognition device 14 comprises a transmitter, a receiver and an antenna for transmitting and receiving electrical radiation, preferably in the microwave range, which is used for detecting and recognizing the target.
  • the space in front of the flat occupancy 16 is completely free, so that after activation of the charge 15, a powerful secondary floor 16 can develop undisturbed under optimal symmetry conditions.
  • the antenna 17 of the target recognition device which is arranged in the rest position within the envelope 9 of the projectile head 10, is to be put into operation at the earliest after the projectile head has been thrown off the load projectile.
  • it is expediently designed to be extendable or foldable.
  • the antenna 17 of the projectile head consists of a dome part 18 which is fixedly arranged in the projectile head and opens in the direction of flight of the projectile head 10 and on which segments 19 which can be folded out in the manner of a screen are articulated.
  • these segments 19 are folded in the rest position and are therefore within the diameter of the envelope 9 of the projectile head 10th
  • Fig. 3 illustrates on the basis of a partial representation of the projectile head 9 the unfolding of the segments 19 and shows the segments 19 in the extended state, whereby together with the fixed cap 18 they form the operational antenna 17.
  • the geometric shape of the antenna 17 is predetermined by the type of radiation characteristic of the antenna desired.
  • the antenna 17 extended in the operating position can have the shape of a paraboloid, in the focal point of which the actual radiator for the electromagnetic energy is arranged, which leads to the transmitter / receiver of the target recognition device 14.
  • This radiator is indicated schematically in FIG. 3 and is designated by reference number 31.
  • the segments 19 of the antenna 17 can be extended in a particularly simple manner by means of articulated rods 30, which are connected on the one hand to each of the segments 19 and on the other hand to a piston 41 (FIG. 4), which in turn is arranged displaceably in a cylinder 40.
  • the displacement of the piston 41 necessary for the unfolding of the segments 19 is expediently effected by an ejection charge 42 which is expediently activated in the target recognition device 14 by a timing element (not shown in more detail).
  • the hinged segments 19 of the antenna 17 lie on the in the idle state Envelope of a folded balloon 50.
  • the balloon 50 is acted upon with gas pressure by a gas generator 51, for example, the gas generator 51 being started by the central target recognition device 14.
  • the balloon 50 can still be used to separate the parts of the envelope 9 of the projectile head 10 which cover the projectile head at the level of the antenna 17 until the antenna 17 is extended.
  • a balloon 50 is provided for detaching the outer wall cladding, which is provided at most on a part of its inner or outer surface with a conductive, preferably metallic coating, which - in the form of a spherical cap - which Represents antenna reflector.
  • an antenna carrier 60 is mounted on an eccentrically arranged axis 61 in the projectile head 10 so that it can be swiveled out in the radial direction, in such a way that it is located within the casing 9 of the projectile head 10 in the idle state.
  • the antenna carrier 60 After the antenna carrier 60 has been swiveled out, which can be caused by ejection charges and / or spring means, the antenna 62 is outside the diameter of the projectile head 10 and can emit electromagnetic energy to the target area or take it from there.
  • this part 61 can also be designed as an antenna carrier for a further antenna, so that the transmitter and receiver of the target recognition device 14 can each be connected to their own antenna.
  • the effective area of the antenna 17 is shaded by the projectile body part in front of it, so that essentially only the antenna area is effective which, viewed in the radial direction, projects beyond the diameter of the warhead.
  • a second reflector 17 ' (FIG. 3a) can be provided in an advantageous further exemplary embodiment of the invention, which reflects the electromagnetic energy generated by the radiator 31 onto the main mirror 18, 19 of the antenna 17 judges. In the case of reception, this second mirror 17 'concentrates the energy absorbed by the antenna 17 onto the radiator 31 which is now acting as a receiver.
  • FIG. 3a A schematic arrangement of this antenna configuration with an indication of the beam path is shown in FIG. 3a.

Abstract

Die Erfindung betrifft einen von einem Lastengeschoß oder Fluggeschoß abwerfbaren Geschoßkopf 10 mit einem einen Sender, enen Empfänger und eine Antenne aufweisenden Zielerkennungsgerät 14 und einer durch ein Zielortungssignal zündbaren Ladung, die ein Sekundärgeschoß auf das erkannte Ziel fortschleudert. Um die Bildung eines durchschlagskräftigen Sekundärgeschosses aus einer mit der zündbaren Ladung 15 verbundenen Flachbelegung 16' nicht zu behindern, wird das Zielerkennungsgerät einschließlich der mit dem Sender bzw. Empfänger des Zielerkennungsgeräts verbindbaren Antenne in Flugrichtung hinter der Ladung 15 angeordnet. Die Antenne wird zweckmäßig ausfahrbar bzw. ausklappbar ausgebildet.The invention relates to a projectile head 10 that can be ejected from a cargo storey or a flight storey, with a target recognition device 14 having a transmitter, a receiver and an antenna, and a charge that can be ignited by a target location signal and hurls a secondary projectile onto the recognized target. In order not to hinder the formation of a penetrating secondary storey from a flat occupancy 16 ′ connected to the ignitable charge 15, the target recognition device including the antenna that can be connected to the transmitter or receiver of the target recognition device is arranged in the flight direction behind the charge 15. The antenna is expediently designed to be extendable or foldable.

Description

Die Erfindung betrifft einen von einem Lastengeschoß oder Flugkörper abwerfbaren Geschoßkopf nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a projectile head that can be ejected from a cargo projectile or missile.

Die Geschoßköpfe der gattungsgemäßen Art werden von einem Lastengeschoß oder Flugkörper ausgestoßen und sinken dann über einem Zielgebiet, von einem Fallschirm gebremst, nieder, wobei sie selbständig ein Ziel, z. B. ein gepanzertes Fahrzeug, erfassen und es nach Erreichen der Bekämpfungsreichweite bekämpfen.The projectile heads of the generic type are ejected from a cargo floor or missile and then sink over a target area, braked by a parachute, whereby they independently a target, for. B. an armored vehicle, capture and combat it after reaching the combat range.

Aus der DE-OS 23 53 566 ist ein abwerfbarer Geschoßkopf bekannt, der zur Bekämpfung des Ziels über eine zündbare Ladung verfügt, die ein Sekundärgeschoß auf das erkannte Ziel fortschleudert. Das Sekundärgeschoß wird dabei aus einer Flachladung gebildet, die in Flugrichtung vor der Zündung zum Sekundärgeschoß verformt wird. Zur Zielerfassung verfügt der abwerfbare Geschoßkopf über ein Zielerkennungsgerät mit einem Sender, einem Empfänger und einer Antenne. Das Zielortungsgerät einschließlich der Antenne und zusätzliche Leitflächen sind in Flugrichtung vor der Flachladung angeordnet. Sie behindern dadurch die Bildung eines optimal geformten Sekundärgeschosses, da sie die Symmetrie der Ladungsanordnung stören und mit ihrer-Masse den Bildungsprozeß des Sekundärgeschosses nachteilig beeinflussen. Das derart gestörte Sekundärgeschoß verfügt über eine nur geringe Reichtweite und mangelnde Durchschlagskraft.From DE-OS 23 53 566 a detachable projectile head is known which has an ignitable charge to combat the target, which hurls a secondary projectile onto the recognized target. The secondary storey is formed from a flat charge that is deformed in the direction of flight before ignition to the secondary storey. The detachable projectile head has a target recognition device with a transmitter, a receiver and an antenna for target acquisition. The target location device including the antenna and additional guide surfaces are arranged in the direction of flight in front of the flat charge. As a result, they hinder the formation of an optimally shaped secondary storey, since they disturb the symmetry of the charge arrangement and, with their mass, adversely affect the formation process of the secondary storey. The secondary floor, which is disturbed in this way, has only a short range and a lack of penetration.

Der Erfindung liegt die Aufgabe zugrunde, einen von einem Lastengeschoß oder Flugkörper abwerfbaren Geschoßkopf anzugeben, der in der Lage ist, ein Sekundärgeschoß mit max. Reichweite und Durchschlagskraft zu erzeugen.The invention has for its object to provide a projectile from a cargo floor or missile projectile head that is able to a secondary floor with max. Generate reach and penetration.

Ausgehend von dem eingangs genannten Geschoßkopf wird diese Aufgabe durch die im Patentanspruch 1 angegebene Erfindung gelöst.Starting from the projectile head mentioned above, this object is achieved by the invention specified in claim 1.

Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung gehen aus den Unteransprüchen hervor.Advantageous refinements and developments of the invention emerge from the subclaims.

Die Erfindung wird nachfolgend unter Bezug auf die Zeichnung näher erläutert. Dabei zeigt:

  • Fig. 1: eine schematische Darstellung des von einem Lastengeschoß oder Flugkörper abgeworfenen Geschoßkopfes 10, der von einem Fallschirm 12 gebremst auf ein Zielgebiet herabsinkt;
  • Fig. 2: eine Teilansicht des Geschoßkopfes, teilweise im Schnitt, mit Darstellung der explosiven Ladung und der Antenne des Zielerkennungsgeräts;
  • Fig. 3: eine Teildarstellung des Geschoßkopfes mit Blick auf die nur teilweise dargestellte Antenne im ausgeklappten Zustand;
  • Fig.3a: ein weiteres Ausführungsbeispiel der Erfindung mit zwei Antennenreflektoren.
  • Fig. 4: eine vergrößerte Teildarstellung zur Erläuterung des Ausklappmechanismus der Antenne;
  • Fig. 5: eine Teildarstellung des Geschoßkoppfes mit einem gasgefüllten Ballon als Ausklappmittel für die Antenne;
  • Fig. 6: zur Erläuterung eines weiteren Ausführungsbeispiels der Erfindung eine schematische Darstellung des Geschoßkopfes mit einem in Radialrichtung ausgeschwenkten Antennenträger;
  • Fig. 7: eine Aufsicht auf den Geschoßkopf nach Fig. 6.
The invention is explained in more detail below with reference to the drawing. It shows:
  • Fig. 1: a schematic representation of the projectile head 10 thrown from a cargo projectile or missile, which is braked down by a parachute 12 to a target area;
  • 2 shows a partial view of the projectile head, partly in section, with an illustration of the explosive charge and the antenna of the target recognition device;
  • Fig. 3: a partial representation of the projectile head with a view of the antenna only partially shown in the unfolded state;
  • 3a: a further embodiment of the invention with two antenna reflectors.
  • 4: an enlarged partial illustration to explain the folding mechanism of the antenna;
  • 5: a partial representation of the projectile head with a gas-filled balloon as a fold-out means for the antenna;
  • 6: to explain a further exemplary embodiment of the invention, a schematic representation of the projectile head with an antenna carrier pivoted out in the radial direction;
  • 7: a top view of the projectile head according to FIG. 6.

Innerhalb der Hülle 9 des Geschoßkopfes 10nach Fig. 1 sind eine Ladung 15, eine darauf angeordnete Flachbelegung 16' zur Bildung eines Sekundärgeschosses 16, ein Zielerkennungsgerät 14 und ein Zünder 13 zur Aktivierung der Ladung 15 angeordnet. Die Verbindungsleinen zwischen dem Geschoßkopf 10 und dem Fall schirm 12 sind mit Bezugsziffer 11 bezeichnet.A charge 15, a flat coating 16 ′ arranged thereon to form a secondary projectile 16, a target recognition device 14 and a detonator 13 for activating the charge 15 are arranged within the casing 9 of the projectile head 10 according to FIG. 1. The connecting lines between the projectile head 10 and the case screen 12 are designated by reference number 11.

Fig. 2 zeigt teilweise geschnitten einen Teilbereich des Geschoßkopfes 10 mit der in Flugrichtung vorn angeordneten Flachbelegung 16', die von einer von einem Zünder 13 aKtivierten Ladung 15 nach Erfassen eines Ziels und Erreichen der Bekämpfungsreichweite zu einem das Ziel zerstörenden Sekundärgeschoß 16 umgewandelt wird. Der Zünder 13 seinerseits ist über eine Zündleitung 13' mit dem Zielerkennungsgerät 14 verbunden, das in Flugrichtung hinter der Flachbelegung 16' und der Ladung 15 angeordnet ist. Das Zielerkennungsgerät 14 umfaßt einen Sender, einen Empfänger sowie eine Antenne zum Aussenden und Empfangen elektrischer Strahlung, vorzugsweise im Mikrowellenbereich, die zum Erfassen und Erkennen des Ziels benutzt wird. Durch die erfindungsgemäße Anordnung des Zielerkennungsgeräts 14 hinter der Ladung, ist der Raum vor der Flachbelegung 16 völlig frei, so daß sich nach Aktivierung der Ladung 15 bei optimalen Symmetriebedingungen ein durchschlagskräftiges Sekundärgeschoß 16 ungestört ausbilden kann. Um ein Aussenden und einen Empfang der elektromagnetischen Energie zu ermöglichen, ist die in Ruhelage innerhalb der Hülle 9 des Geschoßkopfes 10 abschußsicher angeordnete Antenne 17 des Zielerkennungsgeräts frühestens nach dem Abwerfen des Geschoßkopfes vom Lastengeschoß in Funktion zu versetzen. Sie ist dazu zweckmäßig ausfahrbar bzw. ausklappbar ausgebildet.FIG. 2 shows a partial section of the projectile head 10 with the flat occupancy 16 ′ arranged in the front in the flight direction, which is converted by a charge 15 activated by an igniter 13 after detection of a target and reaching the control range to a secondary projectile 16 destroying the target. The igniter 13 in turn is connected via an ignition line 13 'to the target recognition device 14, which is arranged in the direction of flight behind the flat occupancy 16' and the charge 15. The target recognition device 14 comprises a transmitter, a receiver and an antenna for transmitting and receiving electrical radiation, preferably in the microwave range, which is used for detecting and recognizing the target. Due to the inventive arrangement of the target recognition device 14 behind the charge, the space in front of the flat occupancy 16 is completely free, so that after activation of the charge 15, a powerful secondary floor 16 can develop undisturbed under optimal symmetry conditions. In order to enable transmission and reception of the electromagnetic energy, the antenna 17 of the target recognition device, which is arranged in the rest position within the envelope 9 of the projectile head 10, is to be put into operation at the earliest after the projectile head has been thrown off the load projectile. For this purpose, it is expediently designed to be extendable or foldable.

In einem ersten Ausführungsbeispiel der Erfindung besteht die Antenne 17 des Geschoßkopfes aus einem im Geschoßkopf fest angeordneten, sich in Flugrichtung des Geschoßkopfes 10 öffnenden Kalottenteil 18, an der schirmartig ausklappbare Segmente 19 angelenkt sind. In Fig. 2 sind diese Segmente 19 in Ruhestellung eingeklappt und befinden sich daher innerhalb des Durchmessers der Hülle 9 des Geschoßkopfes 10.In a first exemplary embodiment of the invention, the antenna 17 of the projectile head consists of a dome part 18 which is fixedly arranged in the projectile head and opens in the direction of flight of the projectile head 10 and on which segments 19 which can be folded out in the manner of a screen are articulated. In Fig. 2, these segments 19 are folded in the rest position and are therefore within the diameter of the envelope 9 of the projectile head 10th

Fig. 3 verdeutlicht anhand einer Teildarstellung des Geschoßkopfes 9 das Ausklappen der Segmente 19 und zeigt die Segmente 19 in ausgefahrenem Zustand, wobei sie zusammen mit der fest angeordneten Kalotte 18 die betriebsbereite Antenne 17 bilden. Die geometrische Gestalt der Antenne 17 wird durch die Art der gewünschten Strahlungscharakteristik der Antenne vorgegeben. Beispielsweise kann die in Betriebsstellung ausgefahrene Antenne 17 die Gestalt eines Paraboloids haben, in dessen Brennpunkt der eigentliche Strahler für die elektromagnetische Energie angeordnet ist, der zum Sender/Empfänger des Zielerkennungsgeräts 14 führt. Dieser Strahler ist in Fig. 3 schematisch angedeutet und mit Bezugsziffer 31 bezeichnet. Auf besonders einfache Weise lassen sich die Segmente 19 der Antenne 17 durch Gelenkstangen 30 ausfahren, die einerseits mit jedem der Segmente 19 und andererseits mit einem Kolben 41 (Fig. 4) verbunden sind, der wiederum in einem Zylinder 40 verschiebbar angeordnet ist. Die für das Ausklappen der Segmente 19 notwendige Verschiebung des Kolbens 41 wird zweckmäßig durch eine Ausstoßladung 42 bewirkt, die zweckmäßig von einem nicht näher dargestellten Zeitglied im Zielerkennungsgerät 14 aktiviert wird.Fig. 3 illustrates on the basis of a partial representation of the projectile head 9 the unfolding of the segments 19 and shows the segments 19 in the extended state, whereby together with the fixed cap 18 they form the operational antenna 17. The geometric shape of the antenna 17 is predetermined by the type of radiation characteristic of the antenna desired. For example, the antenna 17 extended in the operating position can have the shape of a paraboloid, in the focal point of which the actual radiator for the electromagnetic energy is arranged, which leads to the transmitter / receiver of the target recognition device 14. This radiator is indicated schematically in FIG. 3 and is designated by reference number 31. The segments 19 of the antenna 17 can be extended in a particularly simple manner by means of articulated rods 30, which are connected on the one hand to each of the segments 19 and on the other hand to a piston 41 (FIG. 4), which in turn is arranged displaceably in a cylinder 40. The displacement of the piston 41 necessary for the unfolding of the segments 19 is expediently effected by an ejection charge 42 which is expediently activated in the target recognition device 14 by a timing element (not shown in more detail).

In einem besonders vorteilhaften weiteren Ausführungsbeispiel der Erfindung (Fig. 5) liegen die aufklappbar ausgebildeten Segmente 19 der Antenne 17 im Ruhezustand auf der Hülle eines zusammengefalteten Ballons 50 auf. Zum Aufklappen der Segmente 19 der Antenne 17 wird der Ballon 50 bei - spielsweise von einem Gasgenerator 51 mit Gasdruck beaufschlagt, wobei der Gasgenerator 51 wiederum von dem zentralen Zielerkennungsgerät 14 gestartet wird. In vorteilhafter Doppelfunktion kann dabei der Ballon 50 noch zum Abtrennen der Teile der Hülle 9 des Geschoßkopfes 10 verwendet werden, die bis zum Ausfahren der Antenne 17 den Geschoßkopf in Höhe der Antenne 17 abdecken.In a particularly advantageous further exemplary embodiment of the invention (FIG. 5), the hinged segments 19 of the antenna 17 lie on the in the idle state Envelope of a folded balloon 50. To open the segments 19 of the antenna 17, the balloon 50 is acted upon with gas pressure by a gas generator 51, for example, the gas generator 51 being started by the central target recognition device 14. In an advantageous double function, the balloon 50 can still be used to separate the parts of the envelope 9 of the projectile head 10 which cover the projectile head at the level of the antenna 17 until the antenna 17 is extended.

In einem weiteren besonders einfach und gewichtssparend ausgebildeten Ausführungsbeispiel der Erfindung ist zum Absprengen der Außenwandverkleidung ein Ballon 50 vorgesehen, der höchstens auf einem Teil seiner inneren oder äußeren Oberfläche mit einer leitfähigen, vorzugsweise metallischen Beschichtung versehen ist, die - in Form einer Kalotte ausgestaltet - den Antennenreflektor darstellt.In a further particularly simple and weight-saving embodiment of the invention, a balloon 50 is provided for detaching the outer wall cladding, which is provided at most on a part of its inner or outer surface with a conductive, preferably metallic coating, which - in the form of a spherical cap - which Represents antenna reflector.

In einem letzten Ausführungsbeispiel der Erfindung (Fig. 6, Fig. 7) ist ein Antennenträger 60 an einer exzentrisch angeordneten Achse 61 in Radialrichtung ausschwenkbar im Geschoßkopf 10 gelagert, derart, daß er sich im Ruhezustand innerhalb der Hülle 9 des Geschoßkopfes 10 befindet. Nach dem Ausschwenken des Antennenträgers 60, was durch Ausstoßladungen und/oder Federmittel bewirkt werden kann, befindet sich die Antenne 62 außerhalb des Durchmessers des Geschoßkopfes 10 und kann elektromagnetische Energie zum Zielgebiet abstrahlen bzw. von dort aufnehmen. Aus Symmetriegründen und zur besseren Gewichtsverteilung ist es zweckmäßig, diametral dem Antennenträger 60 gegenüberliegend um eine weitere Schwenkachsae 61' ein gewich-tseäßig dem Antennenträger 60 entsprechendes Teil 61 ausschwenken zu lassen.In a last embodiment of the invention (Fig. 6, Fig. 7), an antenna carrier 60 is mounted on an eccentrically arranged axis 61 in the projectile head 10 so that it can be swiveled out in the radial direction, in such a way that it is located within the casing 9 of the projectile head 10 in the idle state. After the antenna carrier 60 has been swiveled out, which can be caused by ejection charges and / or spring means, the antenna 62 is outside the diameter of the projectile head 10 and can emit electromagnetic energy to the target area or take it from there. For reasons of symmetry and for better weight distribution, it is expedient to have a part 61 corresponding to the weight of the antenna support 60 pivot out diametrically opposite the antenna support 60 by a further pivot axis 61 '.

Für besondere Anwendungsfälle kann jedoch auch dieses Teil 61 als Antennenträger für eine weitere Antenne ausgestaltet sein, so daß Sender und Empfänger des Zielerkennungsgeräts 14 jeweils mit einer eigenen Antenne verbindbar sind.For special applications, however, this part 61 can also be designed as an antenna carrier for a further antenna, so that the transmitter and receiver of the target recognition device 14 can each be connected to their own antenna.

Im Ausführungsbeispiel nach Fig. 3 wird die wirksame Fläche der Antenne 17 durch den davorliegenden Geschoßkörperteil abgeschattet, so daß im wesentlichen nur die Antennenfläche wirksam ist, die - in Radialrichtung gesehen - über den Durchmesser des Gefechtskopfes hinausragt. Um die Abstrahl- und Empfangseigenschaften der Antenne 17 zu verbessern, kann in einem vorteilhaften weiteren Ausführungsbeispiel der Erfindung ein zweiter Reflektor 17' (Fig. 3a) vorgesehen sein, der die vom Strahler 31 erzeugte elektromagnetische Energie auf den Hauptspiegel 18, 19 der Antenne 17 richtet. Im EmpfangsfaLl konzentriert dieser zweite Spiegel 17' die von der Antenne 17 aufgenommene Energie auf den jetzt als Empfänger wirksamen Strahler 31. Eine schematische Anordnung dieser Antennenkonfiguration mit Andeutung des Strahlengangs ist in Fig. 3a dargestellt.In the exemplary embodiment according to FIG. 3, the effective area of the antenna 17 is shaded by the projectile body part in front of it, so that essentially only the antenna area is effective which, viewed in the radial direction, projects beyond the diameter of the warhead. In order to improve the radiation and reception properties of the antenna 17, a second reflector 17 '(FIG. 3a) can be provided in an advantageous further exemplary embodiment of the invention, which reflects the electromagnetic energy generated by the radiator 31 onto the main mirror 18, 19 of the antenna 17 judges. In the case of reception, this second mirror 17 'concentrates the energy absorbed by the antenna 17 onto the radiator 31 which is now acting as a receiver. A schematic arrangement of this antenna configuration with an indication of the beam path is shown in FIG. 3a.

Claims (8)

1. Von einem Lastengeschoß oder Flugkörper abwerfbarer Geschoßkopf mit einem einen Sender, einen Empfänger und eine Antenne aufweisenden Zielerkennungsgerät und einer durch ein Zielortungssignal zündbaren Ladung, die ein Sekundärgeschoß auf das erkannte Ziel fortschleudert, dadurch gekennzeichnet, daß das Zielerkennungsgerät (14) und die Antenne (17) des Zielerkennungsgerätes (14) in Flugrichtung hinter der Ladung (15) angeordnet sind und daß die Antenne (17) ausfahrbar bzw. ausklappbar ausgebildet ist.1. From a cargo floor or missile projectile projectile head with a transmitter, a receiver and an antenna having target detection device and a detonatable by a target location signal charge, which hurls a secondary projectile at the detected target, characterized in that the target detection device (14) and the antenna (17) of the target recognition device (14) are arranged in the flight direction behind the cargo (15) and that the antenna (17) is designed to be extendable or foldable. 2. Geschoßkopf nach Anspruch 1, dadurch gekennzeichnet, daß die Antenne (17) aus einer fest angeordneten Kalotte (18) besteht, an der schirmartig aufklappbare Segmente (19) angelenkt sind.2. projectile head according to claim 1, characterized in that the antenna (17) consists of a fixed calotte (18) on the umbrella-like hinged segments (19) are articulated. 3. Geschoßkopf nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß die Segmente (19) der Antenne (17) über Gelenkstangen (30) mit einem Kolben (41) verbunden sind, der in einem Zylinder (40) vermittels einer von dem Zielerkennungsgerät (14) aktivierten Ausstoßladung (42) angetrieben gleitbar gelagert ist.3. projectile head according to one of claims 1 and 2, characterized in that the segments (19) of the antenna (17) are connected via articulated rods (30) to a piston (41) which in a cylinder (40) by means of one of the Target detection device (14) activated ejection charge (42) is slidably driven. 4. Geschoßkopf nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß zum Ausfahren der Segmente (19) der Antenne (17) ein von einem Gasgenerator (51) aufblasbarer Ballon (50) vorgesehen ist.4. Projectile head according to one of claims 1 and 2, characterized in that a balloon (50) inflatable from a gas generator (51) is provided for extending the segments (19) of the antenna (17). 5. Geschoßkopf nach Anspruch 4, dadurch gekennzeichnet, daß der Ballon (50) in Doppelfunktion zum Absprengen der die Antennensektion des Geschoßkopfes (10) verkleidenden Teile der Hülle (9) des Geschoßkopfes (10) vorgesehen ist.5. Projectile head according to claim 4, characterized in that the balloon (50) is provided in double function for blasting off the parts of the envelope (9) of the projectile head (10) covering the antenna section of the projectile head (10). 6. Geschoßkopf nach einem der Ansprüche 1, 2, 4, 5, dadurch gekennzeichnet, daß der Ballon (50) auf einem eine Kalotte darstellenden Teilbereich seiner inneren und/oder äußeren Oberfläche mit einer leitfähigen Schicht, vorzugsweise einer Metallschicht, bedeckt ist, so daß er als Antennenreflektor wirkt.6. projectile head according to one of claims 1, 2, 4, 5, characterized in that the balloon (50) is covered on a part of its inner and / or outer surface representing a calotte with a conductive layer, preferably a metal layer, so that it acts as an antenna reflector. 7. Geschoßkopf nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß die Antenne (62) in einem um eine exzentrisch angeordnete Drehachse (60') in Radialrichtung ausschwenkbaren Antennenträger (60) angeordnet ist.7. Projectile head according to one of claims 1 and 2, characterized in that the antenna (62) is arranged in an antenna carrier (60) which can be pivoted out in the radial direction about an eccentrically arranged axis of rotation (60 '). B. Geschoßkopf nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß die Antenne (17) zwei Reflektoren (17', 18, 19) umfaßt, deren reflektierende Flächen einander gegenüberstehen und die den Strahler/Empfänger (31) des Zielerkennungsgeräts (14) zwischen sich einschließen.B. projectile head according to one of claims 1 to 7, characterized in that the antenna (17) comprises two reflectors (17 ', 18, 19), the reflecting surfaces of which face each other and which emit the radiator / receiver (31) of the target recognition device (14th ) between themselves.
EP84106683A 1983-06-25 1984-06-12 Projectile head to be launched by a carrier projectile or missile Expired EP0137910B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833322927 DE3322927A1 (en) 1983-06-25 1983-06-25 A projectile that can be ejected from a missile or missile
DE3322927 1983-06-25

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EP0137910A1 true EP0137910A1 (en) 1985-04-24
EP0137910B1 EP0137910B1 (en) 1987-02-11

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US (2) US4622900A (en)
EP (1) EP0137910B1 (en)
DE (2) DE3322927A1 (en)
ES (1) ES8503219A1 (en)
NO (1) NO154811C (en)

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EP0424336A2 (en) * 1989-10-20 1991-04-24 Aktiebolaget Bofors Subwarhead
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EP0252036A3 (en) * 1986-03-27 1988-02-17 Aktiebolaget Bofors Homing submunition
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EP0424337A2 (en) * 1989-10-20 1991-04-24 Aktiebolaget Bofors Subwarhead
EP0424337A3 (en) * 1989-10-20 1992-01-22 Aktiebolaget Bofors Subwarhead
EP0424336A3 (en) * 1989-10-20 1992-02-19 Aktiebolaget Bofors Subwarhead

Also Published As

Publication number Publication date
ES533659A0 (en) 1985-03-01
NO154811C (en) 1986-12-29
US4691636A (en) 1987-09-08
EP0137910B1 (en) 1987-02-11
DE3322927A1 (en) 1985-01-03
ES8503219A1 (en) 1985-03-01
NO842401L (en) 1984-12-27
NO154811B (en) 1986-09-15
DE3462377D1 (en) 1987-03-19
US4622900A (en) 1986-11-18

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