EP0162250B1 - Missile with a remotely operating warhead - Google Patents

Missile with a remotely operating warhead Download PDF

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Publication number
EP0162250B1
EP0162250B1 EP85104077A EP85104077A EP0162250B1 EP 0162250 B1 EP0162250 B1 EP 0162250B1 EP 85104077 A EP85104077 A EP 85104077A EP 85104077 A EP85104077 A EP 85104077A EP 0162250 B1 EP0162250 B1 EP 0162250B1
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EP
European Patent Office
Prior art keywords
missile
warhead
target
charge
head
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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
Application number
EP85104077A
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German (de)
French (fr)
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EP0162250A1 (en
Inventor
Erich Alker
Walter Prof. Diesinger
Rainer Schöffl
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Dynamit Nobel AG
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Dynamit Nobel AG
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Publication date
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Publication of EP0162250A1 publication Critical patent/EP0162250A1/en
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Expired legal-status Critical Current

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    • 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
    • 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
    • F42B12/16—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 in combination with an additional projectile or charge, acting successively on the target

Definitions

  • the invention relates to a missile according to the preamble of patent claim 1.
  • the warhead In order to achieve an optimal effect, the warhead must be detonated at a certain distance from the target, which is about 4 to 10 times the caliber of shaped charges. There must be no components in front of the warhead that could hinder the long-range effect. This condition is difficult to meet with guided missiles, since there is usually a seeker head and the associated electronics at the front end of the warhead.
  • a typical example of such a missile is e.g. B. in "Internationale Wehrrevue", Issue 11/1981, p. 1464.
  • the object of the invention is to provide a missile of the type specified in the preamble of claim 1, in which the warhead is detonated at the prescribed distance before hitting the target without being hindered by components which are otherwise required.
  • the components lying in front of the warhead can be dismantled, for example, by an explosive charge or swung out to the side.
  • an explosive charge or swung out to the side.
  • the repulsion of the elements in the direction of flight can by mechanical force elements, for. B. a compression spring.
  • a pyrotechnic charge is preferably used.
  • the guided missile shown schematically in FIG. 1 has a seeker head 1 with electronics 2 arranged behind it, which is accommodated in a casing 8.
  • the rear end of the shell 8 is connected to the missile shell 6 by shear pins 9.
  • the missile shell 6 forms the jacket of the warhead 3, which in the present case is designed as a shaped charge head and contains a shaped charge 12, the forward-directed shaped charge funnel of which is denoted by 12 '.
  • the control part 4 is housed, from which pivotable rudder 5 protrude.
  • wings 7 are attached to the missile shell 6.
  • a proximity sensor 10, 10 ' which is connected to the electronics 2, is attached to the seeker head 1.
  • a pyrotechnic charge 11 is attached, which in the exemplary embodiment shown extends into the hollow charge funnel 12 '.
  • the proximity sensor 10, 10 ', the z. B. is designed as an optronic sensor, has a transmitting optics 10 and a receiving optics 10 ', which initiate the pyrotechnic charge 11 according to FIG. 2 when reaching a fixed distance A using evaluation electronics.
  • the pressure achieved by the combustion of the charge 11 in the shaped charge cone 12 ' causes the shear pins 9 to shear and the seeker head 1 with electronics 2 to be pushed off to the front.
  • the overlap 13 of the missile shell 6 with the front shell 8 acts like a piston guide, whereby the repulsion speed is improved.
  • Fig. 3 the missile after repelling the seeker head 1 with electronics 2 is shown. These two bodies move away from the rest of the missile 14 at a relative speed corresponding to the repulsion speed.
  • Fig. 4 shows the time of detonation of the warhead 3 in the rest of the missile 14. This time is chosen so that the distance X from the warhead to the target corresponds to the optimal distance desired for the effect.
  • the seeker head 1 with electronics 2 is closed hit the target at this point. Since its partly deformed remains represent a thickening of the target, the optimal distance from the rear edge of these elements was calculated.
  • the penetration rate for armored steel was 2.5 times the caliber. With an optimal distance without a seeker in front of it, the penetration rate could be increased to about 8 times the caliber. Even if the penetration rate is reduced by the seeker located between the target and the warhead at the time of the warhead detonation, the penetration rate increases to at least 7 times the caliber, which corresponds to an improvement of 2.8 times.
  • the warhead 3 is initiated simultaneously with the pyrotechnic charge 11, but that a pyrotechnic delay delays the detonation of the warhead so that it acts at the optimal distance. This requires an essentially constant velocity of the missile in the vicinity of the target. Since this will not always be the case, in an alternative embodiment the warhead is triggered by a contact sensor.
  • FIG. 5 shows an example of this, in which the repelled seeker head 1 with electronics 2 pulls a rod-shaped contact sensor out of the remaining missile 14, the length of the contact sensor 15 corresponding to the distance X required for high-energy penetration.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar Systems Or Details Thereof (AREA)

Description

Die Erfindung betrifft einen Flugkörper nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a missile according to the preamble of patent claim 1.

Flugkörper zur Bekämpfung gepanzerter Ziele weisen in der Regel Gefechtsköpfe auf, die nach dem Hohlladungsprinzip wirken, die das Ziel mittels eines energiereichen Strahles (Hohlladung; Shaped Charge) oder eines Projektils (P-Ladung = projektilbildende Ladung; SFF = Self-Forging Fragment) durchdringen. Um eine optimale Wirkung zu erzielen, muß der Gefechtskopf in einem bestimmten Abstand zum Ziel zur Detonation gebracht werden, der bei Hohlladungen etwa das 4- bis 10-fache des Kalibers beträgt. Dabei dürfen sich vor dem Gefechtskopf keine Bauelemente befinden, die die Entfaltung der Fernwirkung behindern können. Diese Bedingung ist bei Lenkflugkörpern schwierig erfüllbar, da sich am vorderen Ende des Gefechtskopfes in der Regel ein Suchkopf und die dazugehörige Elektronik befinden. Ein typisches Beispiel für einen solchen Flugkörper ist z. B. in "Internationale Wehrrevue", Heft 11/1981, S. 1464, beschrieben.Missiles for combating armored targets generally have warheads which act according to the shaped charge principle and penetrate the target by means of an energy-rich beam (shaped charge; shaped charge) or a projectile (P charge = projectile-forming charge; SFF = self-forging fragment) . In order to achieve an optimal effect, the warhead must be detonated at a certain distance from the target, which is about 4 to 10 times the caliber of shaped charges. There must be no components in front of the warhead that could hinder the long-range effect. This condition is difficult to meet with guided missiles, since there is usually a seeker head and the associated electronics at the front end of the warhead. A typical example of such a missile is e.g. B. in "Internationale Wehrrevue", Issue 11/1981, p. 1464.

Aufgabe der Erfindung ist es, einen Flugkörper, der im Oberbegriff des Patentanspruchs 1 angegebenen Art zu schaffen, bei dem der Gefechtskopf in dem vorgeschriebenen Abstand vor dem Auftreffen auf das Ziel zur Detonation gebracht wird, ohne dabei durch anderweitig erforderliche Bauelemente behindert zu werden.The object of the invention is to provide a missile of the type specified in the preamble of claim 1, in which the warhead is detonated at the prescribed distance before hitting the target without being hindered by components which are otherwise required.

Die Lösung dieserAufgabe erfolgt mit den im kennzeichnenden Teil des Patentanspruchs 1 angegebenen Merkmalen. Danach werden in Zielnähe die vor dem Gefechtskopf befindlichen Bauelemente vom Flugkörper abgestoßen bzw. abgetrennt. Dies kann zwar zur Folge haben, daß der Flugkörper dann keine Lenkkommandos mehr erhält, jedoch sind in dem in Betracht kommenden Entfernungsbereich in der Regel keine Korrekturen der Flugbahn mehr zu erwarten. In einem untersuchten Beispiel, bei dem sich ein Flugkörper mit 100 m/s dem Ziel nähert, hätte der Suchkopf in 3 m Entfernung vom Ziel abgetrennt werden müssen, um 25 ms später den Gefechtskopf bei optimalem Abstand zur Detonation bringen zu können. Es ist einleuchtend, daß in dieser kurzen Zeit keine wirksamen Bahnkorrekturen mehr vorgenommen werden können.This object is achieved with the features specified in the characterizing part of patent claim 1. The components located in front of the warhead are then repelled or detached from the missile near the target. Although this can result in the missile no longer receiving any steering commands, corrections to the trajectory are generally no longer to be expected in the range in question. In an investigated example, in which a missile approaches the target at 100 m / s, the seeker head would have to be separated at a distance of 3 m from the target in order to detonate the warhead at an optimal distance 25 ms later. It is obvious that in this short time no more effective path corrections can be made.

Die vor dem Gefechtskopf liegenden Bauelemente können beispielsweise durch eine Sprengladung zerlegt oder seitlich ausgeschwenkt werden. Es ist jedoch möglich, die Elemente axial, d. h. in Flugrichtung vom Gefechtskopf zubewegung, um störende Kräfte bzw. Momente, die eine Drehung des Flugkörpers um eine der Querachsen bewirken können, zu vermeiden. Das Abstoßen der Elemente in Flugrichtung kann durch mechanische Kraftelemente, z. B. eine Druckfeder, erfolgen. Da es jedoch wünschenswert ist, die Elemente möglichst schnell gegen die z. B. erheblichen Luftkräfte wegzubewegen, wird bevorzugt eine pyrotechnische Ladung verwendet.The components lying in front of the warhead can be dismantled, for example, by an explosive charge or swung out to the side. However, it is possible to axially, i.e. H. move in the direction of flight from the warhead in order to avoid disruptive forces or moments which can cause the missile to rotate about one of the transverse axes. The repulsion of the elements in the direction of flight can by mechanical force elements, for. B. a compression spring. However, since it is desirable to quickly the elements against the z. B. to move away considerable air forces, a pyrotechnic charge is preferably used.

Im folgenden werden unter Bezugnahme auf die Zeichnungen Ausführungsbeispiele der Erfindung näher erläutert.Exemplary embodiments of the invention are explained in more detail below with reference to the drawings.

Es zeigen:

  • Fig. 1 einen schematischen Längsschnitt durch ein Lenkflugkörper,
  • Fig. 2 den Anlug des Lenkflugkörpers auf das Ziel,
  • Fig. 3 den Lenkfiugkörper'nach Abstoßen des Suchkopfes,
  • Fig. 4 den Lenkflugkörper zum Zeitpunkt der Gefechtskopfdetonation und
  • Fig. 5 einen Lenkflugkörper mit herausziehbarem Kontaktfühler.
Show it:
  • 1 shows a schematic longitudinal section through a guided missile,
  • 2 the bearing of the guided missile on the target,
  • 3 shows the steering body after the seeker head has been pushed off,
  • Fig. 4 shows the missile at the time of warhead detonation and
  • Fig. 5 shows a guided missile with a pull-out contact sensor.

Der in Fig. 1 schematisch dargestellte Lenkflugkörper weist am vorderen Ende einen Suchkopf 1 mit dahinter angeordneter Elektronik 2 auf, die in einer Hülle 8 untergebracht ist. Das rückwärtige Ende der Hülle 8 ist mit der Flugkörperhülle 6 durch Scherstifte 9 verbunden. Die Flugkörperhülle 6 bildet den Mantel des Gefechtskopfes 3, der im vorliegenden Fall als Hohlladungskopf ausgebildet ist und eine Hohlladung 12 enthält, deren nach vorne gerichteter Hohlladungstrichter mit 12' bezeichnet ist. Im rückwärtigen Ende der Flugkörperhülle 6 ist der Steuerteil 4 untergebracht, von dem schwenkbare Ruder 5 abstehen. Ferner sind an der Flugkörperhülle 6 Tragflügel 7 befestigt. Am Suchkopf 1 ist ein Annäherungssensor 10, 10' befestigt, der mit der Elektronik 2 in Verbindung steht. Am rückwärtigen Ende des die Elektronik 2 enthaltenden Behälters ist eine pyrotechnische Ladung 11 angebracht, die bei dem dargestellten Ausführungsbeispiel bis in den Hohlladungstrichter 12' hineinragt.The guided missile shown schematically in FIG. 1 has a seeker head 1 with electronics 2 arranged behind it, which is accommodated in a casing 8. The rear end of the shell 8 is connected to the missile shell 6 by shear pins 9. The missile shell 6 forms the jacket of the warhead 3, which in the present case is designed as a shaped charge head and contains a shaped charge 12, the forward-directed shaped charge funnel of which is denoted by 12 '. In the rear end of the missile shell 6, the control part 4 is housed, from which pivotable rudder 5 protrude. Furthermore, wings 7 are attached to the missile shell 6. A proximity sensor 10, 10 ', which is connected to the electronics 2, is attached to the seeker head 1. At the rear end of the container containing the electronics 2, a pyrotechnic charge 11 is attached, which in the exemplary embodiment shown extends into the hollow charge funnel 12 '.

Der Annäherungssensor 10, 10', der z. B. als optronischer Sensor ausgebildet ist, besitzt eine Sendeoptik 10 und eine Empfangsoptik 10', die gemäß Fig. 2 bei Erreichen eines fest eingestellten Abstandes A unter Verwendung einer Auswertelektronik die pyrotechnische Ladung 11 initiiere. Der durch den Abbrand der Ladung 11 im Hohlladungskegel 12' erreichte Druck bewirkt, daß die Scherstifte 9 abscheren und Suchkopf 1 mit Elektronik 2 nach vorne abgestoßen werden. Die Überlappung 13 der Flugkörperhülle 6 mit der vorderen Hülle 8 wirkt dabei wie eine Kolbenführung, wodurch die Abstoßgeschwindigkeit verbessert wird.The proximity sensor 10, 10 ', the z. B. is designed as an optronic sensor, has a transmitting optics 10 and a receiving optics 10 ', which initiate the pyrotechnic charge 11 according to FIG. 2 when reaching a fixed distance A using evaluation electronics. The pressure achieved by the combustion of the charge 11 in the shaped charge cone 12 'causes the shear pins 9 to shear and the seeker head 1 with electronics 2 to be pushed off to the front. The overlap 13 of the missile shell 6 with the front shell 8 acts like a piston guide, whereby the repulsion speed is improved.

In Fig. 3 ist der Flugkörper nach dem Abstoßen des Suchkopfes 1 mit Elektronik 2 dargestellt. Diese beiden Körper entfernen sich mit einer der Abstoßgeschwindigkeit entsprechenden Relativgeschwindigkeit vom restlichen Flugkörper 14.In Fig. 3, the missile after repelling the seeker head 1 with electronics 2 is shown. These two bodies move away from the rest of the missile 14 at a relative speed corresponding to the repulsion speed.

Fig. 4 zeigt den Zeitpunkt der Detonation des Gefechtskopfes 3 im restlichen Flugkörper 14. Dieser Zeitpunkt ist so gewählt, daß der Abstand X vom Gefechtskopf zum Ziel dem für die Wirkung gewünschten optimalen Abstand entspricht. Der Suchkopf 1 mit Elektronik 2 ist zu diesem Zeitpunkt auf das Ziel aufgeprallt. Da seine zum Teil deformierten Reste eine Aufdickung des Zieles darstellen, wurde der optimale Abstand von der Hinterkante dieser Elemente aus gerechnet.Fig. 4 shows the time of detonation of the warhead 3 in the rest of the missile 14. This time is chosen so that the distance X from the warhead to the target corresponds to the optimal distance desired for the effect. The seeker head 1 with electronics 2 is closed hit the target at this point. Since its partly deformed remains represent a thickening of the target, the optimal distance from the rear edge of these elements was calculated.

Um einen 1,6 kg schweren Suchkopf mit etwa 30 m/s vom Flugkörper wegzubewegen, waren in einem untersuchten Fall 7 g Schwarzpulver als pyrotechnische Ladung erforderlich.In order to move a 1.6 kg seeker head away from the missile at approximately 30 m / s, 7 g black powder was required as a pyrotechnic charge in one case examined.

Die erzielte Verbesserung bezüglich der Wirkung des Gefechtskopfes durch die erfindungsgemäße Lösung kann an folgendem Beispiel verdeutlicht werden:The improvement achieved with regard to the effect of the warhead by the solution according to the invention can be illustrated using the following example:

Bei einem Lenkflugkörper mit Hohlladungsgefechtskopf und davor befindlichem Suchkopf betrug die Durchschlagsleistung bei Panzerstahl das 2,5- fache des Kalibers. Bei optimalem Abstand ohne davor befindlichem Suchkopf konnte die Durchschlagsleistung ca. auf das 8-fache des Kalibers gesteigert werden. Selbst bei Verminderung der Durchschlagsleistung durch den zwischen Ziel und Gefechtskopf befindlichen Suchkopf zur Zeit der Gefechtskopfdetonation, bleibt eine Steigerung der Durchschlagsleistung auf mindestens das 7-fache des Kalibers, was eine Verbesserung um das 2,8-fache entspricht.For a guided missile with a shaped charge warhead and a seeker head in front of it, the penetration rate for armored steel was 2.5 times the caliber. With an optimal distance without a seeker in front of it, the penetration rate could be increased to about 8 times the caliber. Even if the penetration rate is reduced by the seeker located between the target and the warhead at the time of the warhead detonation, the penetration rate increases to at least 7 times the caliber, which corresponds to an improvement of 2.8 times.

In dem in Fign. 1 bis 4 dargestellten Beispiel wurde davon ausgegangen, daß der Gefechtskopf 3 gleichzeitig mit der pyrotechnischen Ladung 11 initiiert wird, daß aber eine pyrotechnische Verzögerung die Detonation des Gefechtskopfes so verzögert, daß er im optimalen Abstand wirkt. Dies setzt eine im wesentlichen konstante Geschwindigkeit des Flugkörpers in Zielnähe voraus. Da dies nicht immer der Fall sein wird, wird in einer alternativen Ausführungsform der Gefechtskopf durch einen Kontaktfühler ausgelöst.In the in fig. 1 to 4 illustrated example, it was assumed that the warhead 3 is initiated simultaneously with the pyrotechnic charge 11, but that a pyrotechnic delay delays the detonation of the warhead so that it acts at the optimal distance. This requires an essentially constant velocity of the missile in the vicinity of the target. Since this will not always be the case, in an alternative embodiment the warhead is triggered by a contact sensor.

Fig. 5 zeigt hierfür ein Beispiel, bei dem der abgestoßene Suchkopf 1 mit Elektronik 2 einen stabförmigen Kontaktsensor aus dem restlichen Flugkörper 14 herauszieht, wobei die Länge des Kontaktsensors 15 dem für die energiereiche Durchdringung erforderlichen Abstand X entspricht.5 shows an example of this, in which the repelled seeker head 1 with electronics 2 pulls a rod-shaped contact sensor out of the remaining missile 14, the length of the contact sensor 15 corresponding to the distance X required for high-energy penetration.

Claims (4)

1. Missile, in particular guided missile, with a remotely controlled war head (3), detonatable before hitting the target, e.g. with a hollow charge or projectile forming charge, and constructional elements (1, 2) located in front thereof, such as e.g. a seeker head (1), characterised in that a pyrotechnic charge (11) or a mechanical force element is provided which pushes off the constructional elements (1, 2) located in front of the war head (3) by a fixed distance on approach to the target in the course of flight, before the war head (3) is detonated before reaching the target, with the pyrotechnic charge (11) or the mechanical force element being initiated by a contact free distance sensor (10, 10').
2. Missile according to claim 1, characterised in that the war head (3) and the pyrotechnic charge (11) are initiated simultaneously and the detonation of the war head (3) takes place delayed by a delay component
3. Missile according to claim 1, characterised in that the war head (3) is triggered by means of a mechanical distance sensing element (15).
4. Missile according to claim 3, characterised in that the mechanical distance sensing element (15) is brought into its operating position by means of the constructional elements which have been pushed off.
EP85104077A 1984-04-17 1985-04-03 Missile with a remotely operating warhead Expired EP0162250B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843414414 DE3414414A1 (en) 1984-04-17 1984-04-17 Missile with a remote-action warhead
DE3414414 1984-04-17

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EP0162250A1 EP0162250A1 (en) 1985-11-27
EP0162250B1 true EP0162250B1 (en) 1988-09-21

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DE (2) DE3414414A1 (en)

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DE3414414A1 (en) 1985-10-17
EP0162250A1 (en) 1985-11-27
DE3565178D1 (en) 1988-10-27
US4823700A (en) 1989-04-25

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