EP0049778B1 - Method for the distribution of ammunition - Google Patents

Method for the distribution of ammunition Download PDF

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Publication number
EP0049778B1
EP0049778B1 EP81107358A EP81107358A EP0049778B1 EP 0049778 B1 EP0049778 B1 EP 0049778B1 EP 81107358 A EP81107358 A EP 81107358A EP 81107358 A EP81107358 A EP 81107358A EP 0049778 B1 EP0049778 B1 EP 0049778B1
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EP
European Patent Office
Prior art keywords
distribution unit
sub
flight
bodies
arrangement
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
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EP81107358A
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German (de)
French (fr)
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EP0049778A1 (en
Inventor
Walter Prof.Dr. Diesinger
Klaus Fischer
Heinz Kroschel
Rolf Menne
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Huels Troisdorf AG
Dynamit Nobel AG
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Huels Troisdorf AG
Dynamit Nobel AG
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Publication of EP0049778A1 publication Critical patent/EP0049778A1/en
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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
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles

Definitions

  • the invention relates to a method for distributing war bodies in accordance with the preamble of claim 1.
  • Cluster munitions e.g. B. for mining the site, can be distributed by means of the ejection head described in DE-A-21 53 994, which is used in particular in connection with rockets and as a distribution unit, a payload carrier plate with several pivotally attached ejector pipes, which to the target area distributing body contain and be spread apart before distribution.
  • the distribution unit is released before the release. H. the beginning of the ejection or distribution of the ejection body by additional braking measures, for example by means of a brake parachute or by airbrakes in flight, braked so that it sinks vertically downward and has thus been transferred to a predetermined release position.
  • the distribution unit can still be connected to the remaining rocket or can also be separated from it and transferred to the vertical path on its own.
  • cluster munitions The effectiveness of cluster munitions is limited by the accuracy of the clarification of the moving targets to be combated and the possibility of being able to predict the paths of the targets with sufficient probability.
  • a disadvantage of every cluster ammunition is the only statistical hit probability, i.e. H. many active bodies reach no goal.
  • Guided missiles represent an expensive weapon with comparatively low cost effectiveness, the effectiveness of which is also limited by the accuracy of the reconnaissance and which require a great deal of effort not only in terms of electronics, but also for the drive.
  • End-phase guided missiles have the advantage over the guided missiles of simplifying the means of transport, in particular an unguided rocket as with cluster munitions.
  • the advantage over the latter is the increase in the probability of hitting in the final phase, i.e. H. shortly before the target by means of a simplified steering compared to conventional guided missiles. Since only the final phase is directed, the goal must be known comparatively precisely, just as with cluster munitions.
  • certain problems in the final phase steering have not yet been solved, e.g. B. the prevention of multiple bombardment of a target by several articulated missiles, a problem that also exists with conventional guided missiles. The problem of multiple bombardment arises particularly when, because of the total costs and / or the range of fire, several missile-guided missiles are fired into the target area with a rocket.
  • the invention has for its object to provide a method for distributing missiles with active charges to the fighter of in particular armored targets, in which two or more daughter missiles representing the missiles are transported together and distributed there by means of a carrier missile, without the above-mentioned Disadvantages occur, d. H. in which a more favorable ratio between the effort required and the attainable probability of being achieved is achieved.
  • the object is achieved on the basis of the method specified in the preamble of claim 1 in accordance with the characterizing part of this claim.
  • the determination of the time of release of the individual daughter missiles depending on the target acquisition by means of the central search and evaluation device on the distribution unit enables an optimal starting or starting position for each individual daughter missile in the target assigned to it by the search and evaluation device. This results in a significant increase in the probability of being hit without the need for a search and evaluation device on each individual daughter missile, as in the case of missiles guided in the final phase.
  • the use of only one central electronic search and evaluation device per distribution unit also makes it possible to design this device with still higher overall expenditure and with a higher performance than the corresponding separate devices of the daughter missiles.
  • Another advantage is the extension of the target phase that can be determined autonomously by the search device, ie. H. the period of time until the release of the daughter missile, which enables a longer target tracking and thus an optimization of the start coordinates of the individual daughter missiles.
  • the carrier missile is preferably a rocket, in particular an unguided rocket. But there are also other unmanned missiles, e.g. B. those with an air-breathing drive or projectiles in question.
  • the distribution unit or distribution structure of the carrier missile can preferably be separated from it before the additional braking measures are taken. Two or more separable distribution units per carrier missile can also be provided.
  • the daughter missiles which are designed as combat bodies to combat moving targets, are housed in or on the distribution unit by z. B. arranged in discharge pipes or on start rails or attached by means of notching devices.
  • the search device is designed in a known manner, for example as an optical or infrared sensor, but preferably as a radar sensor.
  • the likewise known electronic evaluation device arranged downstream of the sensor has at least one computer with a storage device.
  • the use of a more sophisticated sensor is provided according to claim 2, which works already in the launch phase of the carrier missile and does not first respond to the individual targets to be fought, but rather can detect a target area formed from several individual targets from a greater distance, which is only resolved by the sensor when the sensor approaches the individual targets.
  • the desired braking of the distribution unit and its preferred separation from the rest of the carrier missile are then triggered in an optimal manner.
  • This central search and evaluation device thus enables an autonomous determination of the times for the braking of the distribution unit and for the release of the daughter missiles and thus an independent correction of reconnaissance errors and the missile scatter.
  • a pre-phase guidance for the daughter missiles can be carried out after detecting the target area, in that for the carrier missile or the distribution unit separate therefrom a within the framework of the aeroballistic, ie. H. aerodynamic and ballistic possibilities optimal descent path is calculated, which by adjustable aerodynamic surfaces such as paraglider, wing etc. or z. B. can also be achieved by control nozzles. This allows an even more precise approximation to the area to be combated, in particular to an accumulation of individual targets in this area, in an advantageous manner.
  • a central search and command device is arranged on the carrier missile or on the distribution unit for the individual daughter missiles to be released one after the other, there are various possibilities for their separation.
  • the daughter missile can be ejected by means of a pyrotechnic charge from launch tubes attached to the distribution unit.
  • this simple solution is associated with reaction forces which cause the distribution unit or the carrier missile to oscillate after the individual launches.
  • the consideration of these pendulum movements when the subsequent daughter missiles are released by the computer of the search and command device can make the system undesirably complex, while an increased aerodynamic damping of the arrangement affects the system time, i. H. can make the period of time until the pendulum movement calms down sufficiently for the next launch.
  • the launch tubes, start rails or the like can be provided so as to be pivotable about the center of gravity of the distribution structure and to assign the daughter missiles to them - together with a compensation mass that may be provided that their focus coincides with that of the distribution structure.
  • This ensures that there is no shift in the center of gravity in the axial direction, ie. H. comes in the longitudinal direction of the distribution unit.
  • This applies to the observation in a side view of the distribution unit, in which the launch tubes, start rails or the like can be pivoted, so to speak, about the height coordinate of the center of gravity of the distribution unit.
  • the launch tubes, starting rails or the like cannot be arranged in one plane, but have to be slightly offset from one another, there is still a shift in the center of gravity in the lateral direction, which is, however, slight.
  • the demands on the daughter missiles are comparatively low.
  • the child missiles or child projectiles are therefore preferably unguided.
  • the task and the result of a possible system analysis are possible combinations that range, for example, from the targeted laying of cluster munitions and the launching of armored fighter-like missiles to simple orbit correction devices for the daughter missiles. But even daughter missiles that are directed to the final phase can be distributed using the method according to the invention, if this proves to be advantageous despite the effort in terms of the target probability.
  • the range of spread is not fixedly predetermined before the launch vehicle is fired, but is instead determined autonomously by the central search and evaluation device.
  • the carrier missile not shown, preferably an unguided rocket, is launched by means of the launcher 1 below the elevation 6 0 and moves on the orbit A.
  • the targets to be combated are assumed in the target area Z due to previous reconnaissance, it is known in Due to appropriate data input prior to launch, the head containing the distribution unit was separated from the rest of the carrier missile at point I and delayed, for example by means of a parachute or brake flaps, to point 11, at which the path speed was reduced sufficiently and the path inclination was so close to the vertical that accordingly DE-A-21 53 994 the launch tubes of the distribution unit can be spread apart.
  • the ogive 2 of the head or the distribution unit 3, which is only indicated by dashed lines in FIG. 2, is separated with a brake parachute 4, so that the search head 5, which is firmly connected to the distribution unit, already has a correspondingly large target area from a great height Z can capture.
  • the descent path of the distribution unit 3, which is optimal within the scope of the aeroballistic possibilities and which can be achieved by means of a paraglider or other correspondingly adjustable asymmetrical aerodynamic surfaces, is then preferably calculated via a computer connected to the search head 5.
  • the launch tubes 6, each with a subsidiary floor located therein are spread apart, which further reduces the speed of the distribution unit.
  • the distribution unit 3 has the configuration K shown in FIG. 2 and is located at a height h above the target area Z. From this height, the targets on the outer edge of the ' target area can first be passed due to the aeroballistic behavior of the subsidiary storeys stored in the computer The choice of a suitable time for shooting. Since the target area is a surface, all outer lines can be detected by a slight rotation of the distribution unit about its longitudinal axis 7. The necessary torque. ment about the longitudinal axis is preferably aerodynamically, for. B. generated by the parachute 4. The targets further in the center of the target area Z can be fought if the warhead has sunk further.
  • the processes at point I can be triggered autonomously by the search device when the target area Z is located.
  • This determination of the target coordinates only shortly before the combat is particularly advantageous in the case of targets that move quickly because - as shown in FIG. 1 - different target areas Z or Z on the same primary trajectory A, depending on the trigger points I or I 'and 11 or II' 'can be recorded.
  • the warhead is again at a height h above the target area Z', from which the targets according to FIG. 2 can be combated.
  • FIG. 3 shows a distribution unit 3 with a brake parachute 4 and a search evaluation device 5, the launch tubes 6 of which can be pivoted about their center of gravity S and that of the distribution unit 3. To simplify the drawing, only two launch tubes 6 arranged closely one behind the other are shown in their extended position.
  • the daughter missiles are also arranged within the launch tubes so that their center of gravity coincides with that of the distribution unit in the drawing plane, there is no ver when a daughter missile is launched shift of the center of gravity in the direction of the longitudinal axis 7.
  • the shift in the center of gravity due to the arrangement of the launch tubes 6 one behind the other is small, so that pendulum movements of the distribution unit 3 due to mass changes are largely eliminated.
  • the daughter missiles can be provided with simple correction devices for their trajectory. According to FIG. 4, a distribution unit 3 can then be used with launch tubes 6 that are only slightly or even not spread outwards, whereby the lateral shift in the center of gravity that occurs after a launch is advantageously kept small.
  • the daughter missiles can be provided with fold-out oars (control surfaces) so that they move on the trajectory B, while the distribution unit 3 moves on the vertical descent path C.
  • the separation from the tube 4 and flying through the web B can be done solely by the weight or supplemented by a drive.
  • the lateral distance of the daughter missiles on orbit B from the vertical orbit C of distribution unit 3, which is necessary to combat the targets, can be achieved, as in FIG. 2, by the ejection height and / or by varying the rudder setting angle.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Description

Die Erfindung betrifft ein Verfahren zum Verteilen von Gefechtskörpern entsprechend dem Oberbegriff des Anspruchs 1.The invention relates to a method for distributing war bodies in accordance with the preamble of claim 1.

Es ist bekannt, bewegliche insbesondere gepanzerte Ziele beispielsweise durch Streumunition, Lenkflugkörper oder in der Entwicklung befindliche endphasengelenkte Flugkörper zu bekämpfen (Siehe z. B. DE-A-2 347 374).It is known to combat movable, in particular armored targets, for example by cluster munitions, guided missiles or end-phase guided missiles under development (see, for example, DE-A-2 347 374).

Streumunition, z. B. zur Verminung des Geländes, kann mittels des in der DE-A-21 53 994 beschriebenen Auswurfkopfes verteilt werden, der insbesondere in Verbindung mit Raketen verwendet wird und als Verteileinheit eine Nutzlastträgerplatte mit mehreren schwenkbar daran angebrachten Ausstoßrohren aufweist, welche die im Zielgebiet zu verteilenden Körper enthalten und vor der Verteilung auseinandergespreizt werden. Um eine kreisförmige Verteilung der Auswurfkörper am Boden zu erreichen, wird die Verteileinheit vor der Freigabe, d. h. dem Beginn des Ausstoßens oder Verteilens der Auswurfkörper durch zusätzliche Bremsmaßnahmen etwa mittels eines Bremsfallschirms oder durch Bremsklappen im Fluge so abgebremst, daß sie senkrecht nach unten sinkt und damit in eine vorgegebene Freigabeposition überführt worden ist. Dabei kann die Verteileinheit noch mit der restlichen Rakete verbunden oder auch von dieser abgetrennt sein und für sich allein in die senkrechte Bahn überführt werden.Cluster munitions, e.g. B. for mining the site, can be distributed by means of the ejection head described in DE-A-21 53 994, which is used in particular in connection with rockets and as a distribution unit, a payload carrier plate with several pivotally attached ejector pipes, which to the target area distributing body contain and be spread apart before distribution. In order to achieve a circular distribution of the ejection bodies on the floor, the distribution unit is released before the release. H. the beginning of the ejection or distribution of the ejection body by additional braking measures, for example by means of a brake parachute or by airbrakes in flight, braked so that it sinks vertically downward and has thus been transferred to a predetermined release position. In this case, the distribution unit can still be connected to the remaining rocket or can also be separated from it and transferred to the vertical path on its own.

Die Wirkung der Streumunition wird begrenzt durch die Genauigkeit der Aufklärung der zu bekämpfenden beweglichen Ziele und die Möglichkeit, die Wege der Ziele mit genügender Wahrscheinlichkeit voraussagen zu können. Ein Nachteil jeder Streumunition ist die nur statistische Treffwahrscheinlichkeit, d. h. viele Wirkkörper erreichen kein Ziel.The effectiveness of cluster munitions is limited by the accuracy of the clarification of the moving targets to be combated and the possibility of being able to predict the paths of the targets with sufficient probability. A disadvantage of every cluster ammunition is the only statistical hit probability, i.e. H. many active bodies reach no goal.

Lenkflugkörper stellen eine teure Waffe mit vergleichsweise geringer Kostenwirksamkeit dar, deren Wirkung gleichfalls durch die Genauigkeit der Aufklärung begrenzt wird und die einen hohen Aufwand nicht nur bezüglich der Elektronik, sondern auch für den Antrieb erfordern.Guided missiles represent an expensive weapon with comparatively low cost effectiveness, the effectiveness of which is also limited by the accuracy of the reconnaissance and which require a great deal of effort not only in terms of electronics, but also for the drive.

Endphasengelenkte Flugkörper haben gegenüber den Lenkflugkörpern den Vorteil der Vereinfachung des Transportmittels, insbesondere einer ungelenkten Rakete wie bei der Streumunition. Der Vorteil gegenüber letzterer ist die Erhöhung der Treffwahrscheinlichkeit in der Endphase, d. h. kurz vor dem Ziel mittels einer gegenüber den herkömmlichen Lenkflugkörpern vereinfachten Lenkung. Da nur die Endphase gelenkt ist, muß aber auch hier ebenso wie bei der Streumunition das Ziel vergleichsweise genau bekannt sein. Weiterhin sind gewisse Probleme bei der Endphasenlenkung noch nicht gelöst, z. B. die Verhinderung des Mehrfachbeschusses eines Zieles durch mehrere endphasengelenkte Flugkörper, ein Problem, das auch bei den herkömmlichen Lenkflugkörpern besteht. Das Problem des Mehrfachbeschusses besteht besonders dann, wenn wegen der Gesamtkosten und/oder der Schußweite mehrere endphasengelenkte Flugkörper mit einer Rakete in das Zielgebiet geschossen werden.End-phase guided missiles have the advantage over the guided missiles of simplifying the means of transport, in particular an unguided rocket as with cluster munitions. The advantage over the latter is the increase in the probability of hitting in the final phase, i.e. H. shortly before the target by means of a simplified steering compared to conventional guided missiles. Since only the final phase is directed, the goal must be known comparatively precisely, just as with cluster munitions. Furthermore, certain problems in the final phase steering have not yet been solved, e.g. B. the prevention of multiple bombardment of a target by several articulated missiles, a problem that also exists with conventional guided missiles. The problem of multiple bombardment arises particularly when, because of the total costs and / or the range of fire, several missile-guided missiles are fired into the target area with a rocket.

Der Erfindung liegt die Aufgabe zugrunde, ein Verfahren zum Verteilen von Gefechtskörpern mit Wirkladungen zum Bekämpfer von insbesondere gepanzerten Zielen anzugeben, bei dem mittels eines Trägerflugkörpers zwei oder mehrere, die Gefechtskörper darstellenden Tochterflugkörper gemeinsam ins Zielgebiet transportiert und dort verteilt werden, ohne daß die vorstehend angegebenen Nachteile auftreten, d. h. bei dem ein günstigeres Verhältnis zwischen erforderlichem Aufwand und erzielbarer Treffwahrscheinlichkeit erreicht wird.The invention has for its object to provide a method for distributing missiles with active charges to the fighter of in particular armored targets, in which two or more daughter missiles representing the missiles are transported together and distributed there by means of a carrier missile, without the above-mentioned Disadvantages occur, d. H. in which a more favorable ratio between the effort required and the attainable probability of being achieved is achieved.

Die Aufgabe wird erfindungsgemäß ausgehend von dem im Oberbegriff des Anspruchs 1 angegebenen Verfahren entsprechend dem Kennzeichen dieses Anspruchs gelöst. Die Festlegung des Zeitpunktes der Freigabe der einzelnen Tochterflugkörper in Abhängigkeit von der Zielerfassung mittels der zentralen Such- und Auswerteeinrichtung an der Verteileinheit ermöglicht eine optimale Start- oder Ausgangsposition für jeden einzelnen Tochterflugkörper in das ihm von der Such- und Auswerteeinrichtung zugeordnete Ziel. Damit wird eine erhebliche Erhöhung der Treffwahrscheinlichkeit erreicht, ohne daß dazu wie bei endphasengelenkten Flugkörpern je eine Such- und Auswerteeinrichtung an jedem einzelnen Tochterflugkörper notwendig ist. Die Verwendung nur einer zentralen elektronischen Such- und Auswerteeinrichtung je Verteileinheit ermöglicht es darüber hinaus, diese eine Einrichtung bei immer noch geringerem Gesamtaufwand mit einem höheren Leistungsvermögen auszubilden als die entsprechenden separaten Einrichtungen der Tochterflugkörper. Ein weiterer Vorteil ist die durch die Sucheinrichtung autonom festlegbare Verlängerung der Zielphase, d. h. der Zeitspanne bis zur Freigabe der Tochterflugkörper, welche eine längere Zielverfolgung und damit eine Optimierung der Startkoordinaten der einzelnen Tochterflugkörper ermöglicht.According to the invention, the object is achieved on the basis of the method specified in the preamble of claim 1 in accordance with the characterizing part of this claim. The determination of the time of release of the individual daughter missiles depending on the target acquisition by means of the central search and evaluation device on the distribution unit enables an optimal starting or starting position for each individual daughter missile in the target assigned to it by the search and evaluation device. This results in a significant increase in the probability of being hit without the need for a search and evaluation device on each individual daughter missile, as in the case of missiles guided in the final phase. The use of only one central electronic search and evaluation device per distribution unit also makes it possible to design this device with still higher overall expenditure and with a higher performance than the corresponding separate devices of the daughter missiles. Another advantage is the extension of the target phase that can be determined autonomously by the search device, ie. H. the period of time until the release of the daughter missile, which enables a longer target tracking and thus an optimization of the start coordinates of the individual daughter missiles.

Bei dem Trägerflugkörper handelt es sich vorzugsweise um eine Rakete, insbesondere eine ungelenkte Rakete. Es kommen aber auch andere unbemannte Flugkörper, z. B. solche mit einem luftatmenden Antrieb oder auch Geschosse, in Frage. Die Verteileinheit oder Verteilstruktur des Trägerflugkörpers ist vorzugsweise von diesem vor Einsetzen der zusätzlichen Bremsmaßnahmen abtrennbar. Es können auch zwei oder mehrere abtrennbare Verteileinheiten je Trägerflugkörper vorgesehen sein. Die Tochterflugkörper, die als Gefechtskörper zur Bekämpfung beweglicher Ziele ausgebildet sind, werden in bzw. an der Verteileinheit untergebracht, indem sie z. B. in Ausstoßrohren oder auf Startschienen angeordnet oder auch mittels Ausklinkvorrichtungen angehängt werden. Die Sucheinrichtung ist in bekannter Weise beispielsweise als optischer oder Infrarot-Sensor, vorzugsweise jedoch als Radar-Sensor ausgebildet. Die dem Sensor nachgeordnete gleichfalls bekannte elektronische Auswerteeinrichtung weist wenigstens einen Rechner mit Speichereinrichtung auf.The carrier missile is preferably a rocket, in particular an unguided rocket. But there are also other unmanned missiles, e.g. B. those with an air-breathing drive or projectiles in question. The distribution unit or distribution structure of the carrier missile can preferably be separated from it before the additional braking measures are taken. Two or more separable distribution units per carrier missile can also be provided. The daughter missiles, which are designed as combat bodies to combat moving targets, are housed in or on the distribution unit by z. B. arranged in discharge pipes or on start rails or attached by means of notching devices. The search device is designed in a known manner, for example as an optical or infrared sensor, but preferably as a radar sensor. The likewise known electronic evaluation device arranged downstream of the sensor has at least one computer with a storage device.

In zweckmäßiger Ausgestaltung der Erfindung ist nach Anspruch 2 die Verwendung eines höher entwickelten Sensors vorgesehen, der bereits in der Startphase des Trägerflugkörpers arbeitet und nicht erst auf die zu bekämpfenden Einzelziele anspricht, sondern schon aus größerer Entfernung einen aus mehreren Einzelzielen gebildeten Zielbereich zu erfassen vermag, der erst bei weiterer Annäherung vom Sensor in die Einzelziele aufgelöst wird. In abhängigkeit von der Erkennung des Zielbereiches werden dann die gewollte Abbremsung der Verteileinheit und deren bevorzugte Trennung vom restlichen Trägerflugkörper in optimaler Weise ausgelöst. Diese zentrale Such- und Auswerteeinrichtung ermöglicht also eine autonome Festlegung der Zeitpunkte für die Abbremsung der Verteileinheit und für die Freigabe der Tochterflugkörper und damit eine selbständige Korrektur von Aufklärungsfehlern und der Raketenstreuung.In an expedient embodiment of the invention, the use of a more sophisticated sensor is provided according to claim 2, which works already in the launch phase of the carrier missile and does not first respond to the individual targets to be fought, but rather can detect a target area formed from several individual targets from a greater distance, which is only resolved by the sensor when the sensor approaches the individual targets. Depending on the detection of the target area, the desired braking of the distribution unit and its preferred separation from the rest of the carrier missile are then triggered in an optimal manner. This central search and evaluation device thus enables an autonomous determination of the times for the braking of the distribution unit and for the release of the daughter missiles and thus an independent correction of reconnaissance errors and the missile scatter.

Gemäß einem weiteren im Anspruch 3 angegebenen Vorschlag der Erfindung kann nach Erfassen des Zielbereiches eine Vorphasenlenkung für die Tochterflugkörper durchgeführt werden, indem für den Trägerflugkörper bzw. die von diesem getrennte Verteileinheit eine in Rahmen der aeroballistischen, d. h. aerodynamischen und ballistischen Möglichkeiten optimale Abstiegsbahn berechnet wird, die durch einstellbare aerodynamische Flächen wie Gleitschirm, Flügel usw. oder z. B. auch durch Steuerdüsen erreicht werden kann. Damit kann in vorteilhafter Weise eine noch weitere genauere Annäherung an den zu bekämpfenden Bereich, insbesondere auch an eine Häufung von Einzelzielen in diesem Bereich, erreicht werden.According to a further proposal of the invention specified in claim 3, a pre-phase guidance for the daughter missiles can be carried out after detecting the target area, in that for the carrier missile or the distribution unit separate therefrom a within the framework of the aeroballistic, ie. H. aerodynamic and ballistic possibilities optimal descent path is calculated, which by adjustable aerodynamic surfaces such as paraglider, wing etc. or z. B. can also be achieved by control nozzles. This allows an even more precise approximation to the area to be combated, in particular to an accumulation of individual targets in this area, in an advantageous manner.

Eine sehr einfache und zuverlässige Methode zur Elimination von Overkill ist im Anspruch 4 angegeben, gemäß dem die Zielkoordinaten eines freigegebenen Tochterflugkörpers in der Auswerteeinrichtung erfaßt, gegebenenfalls entsprechend der weiteren Abstiegsbahn der Verteileinheit korrigiert, und als erneutes Ziel gesperrt werden.A very simple and reliable method for eliminating overkill defined in claim 4, according to which the target coordinates of a released daughter f lugkörpers in the evaluation device detects optionally correspondingly corrects the further descent path of the distribution unit, and be locked as a renewed target.

Bei der Anordnung einer zentralen Such- und Kommandoeinrichtung am Trägerflugkörper bzw. an der Verteileinheit für die nacheinander freizugebenden einzelnen Tochterflugkörper gibt es für deren Trennung verschiedene Möglichkeiten. So kann der Tochterflugkörper mittels einer pyrotechnischen Ladung aus an der Verteileinheit angebrachten Abschußrohren ausgestoßen werden. Diese einfache Lösung ist jedoch mit Reaktionskräften verbunden, die ein Pendeln der Verteileinheit bzw. des Trägerflugkörpers nach den einzelnen Abschüssen hervorrufen. Die Berücksichtigung dieser Pendelbewegungen bei der Freigabe der nachfolgenden Tochterflugkörper durch den Rechner der Such- und Kommandoeinrichtung kann das System unerwünscht komplex machen, während eine verstärkte aerodynamische Bedämpfung der Anordnung die Systemzeit, d. h. die Zeitspanne bis zu einer für den nächsten Abschuß hinreichenden Beruhigung der Pendelbewegung ungünstig lang machen kann.When a central search and command device is arranged on the carrier missile or on the distribution unit for the individual daughter missiles to be released one after the other, there are various possibilities for their separation. The daughter missile can be ejected by means of a pyrotechnic charge from launch tubes attached to the distribution unit. However, this simple solution is associated with reaction forces which cause the distribution unit or the carrier missile to oscillate after the individual launches. The consideration of these pendulum movements when the subsequent daughter missiles are released by the computer of the search and command device can make the system undesirably complex, while an increased aerodynamic damping of the arrangement affects the system time, i. H. can make the period of time until the pendulum movement calms down sufficiently for the next launch.

Derartige Reaktionskräfte werden vermieden, wenn die Trennung der Tochterflugkörper vom Trägerflugkörper bzw. der Verteileinheit aufgrund ihres Eigengewichtes erfolgt. Eine zumindest nahezu rückstoßfreie Trennung mit in vorteilhafter Weise höherer Abgangsgeschwindigkeit ist möglich, wenn der Tochterflugkörper nach Anspruch 5 mit Hilfe eines Raketenantriebes gestartet bzw. nach dem Prinzip der Daviskanone gleichzeitig mit einer in entgegengesetzter Richtung ausstoßbaren Kompensationsmasse aus dem Abschußrohr abgefeuert wird. Jedoch tritt auch hier eine geringe Pendelung auf, weil sich durch die nacheinander erfolgende Freigabe der Tochterflugkörper die Schwerpunktslage der mit den restlichen Tochterflugkörpern versehenen Struktur ändert.Such reaction forces are avoided if the daughter missiles are separated from the carrier missile or the distribution unit due to their own weight. An at least almost recoil-free separation with an advantageously higher exit speed is possible if the daughter missile is launched with the aid of a rocket drive or, according to the principle of the Davis cannon, is simultaneously fired from the launch tube with a compensation mass that can be ejected in the opposite direction. However, a slight oscillation also occurs here because the successive release of the daughter missiles changes the center of gravity of the structure provided with the remaining daughter missiles.

Sofern es im Einzelfall zweckmäßig sein sollte, einen solchen Störeinfluß zu minimieren, kann nach Anspruch 6 vorgesehen werden, die Abschußrohre, Startschienen od. dgl. um den Schwerpunkt der Verteilstruktur verschwenkbar anzuordnen und ihnen die Tochterflugkörper - zusammen mit einer gegebenenfalls vorgesehenen Kompensationsmasse - so zuzuordnen, daß deren Schwerpunkt mit dem der Verteilstruktur zusammenfällt. Damit ist sichergestellt, daß es durch die Freigabe der Tochterflugkörper zu keiner Schwerpunktsverschiebung in axialer Richtung, d. h. in Längsrichtung der Verteileinheit kommt. Dies gilt für die Betrachtung in einer Seitenansicht der Verteileinheit, in welcher die Abschußrohre, Startschienen od. dgl. sozusagen um die Höhenkoordinate des Schwerpunktes der Verteileinheit verschwenkbar sind. Im Hinblick darauf, daß die Abschußrohre, Startschienen od. dgl. dabei nicht in einer Ebene angeordnet werden können, sondern geringfügig gegeneinander versetzt werden müssen, tritt noch eine Schwerpunktsverschiebung in seitlicher Richtung auf, die jedoch gering ist.If it should be expedient in individual cases to minimize such an interference, it can be provided according to claim 6 to arrange the launch tubes, start rails or the like so as to be pivotable about the center of gravity of the distribution structure and to assign the daughter missiles to them - together with a compensation mass that may be provided that their focus coincides with that of the distribution structure. This ensures that there is no shift in the center of gravity in the axial direction, ie. H. comes in the longitudinal direction of the distribution unit. This applies to the observation in a side view of the distribution unit, in which the launch tubes, start rails or the like can be pivoted, so to speak, about the height coordinate of the center of gravity of the distribution unit. In view of the fact that the launch tubes, starting rails or the like cannot be arranged in one plane, but have to be slightly offset from one another, there is still a shift in the center of gravity in the lateral direction, which is, however, slight.

Bei dem erfindungsgemäßen Verfahren sind die Anforderungen an die Tochterflugkörper vergleichsweise gering. Bevorzugt sind die Tochterflugkörper oder Tochtergeschosse daher ungelenkt. Als Tochterflugkörper können z. B. Streumunition wie Minen, Bomblets od. dgl., geschoßartige Körper, Gefechtskörper mit zusätzlichem Antrieb usw. eingesetzt werden. Je nach. Aufgabenstellung und Ergebnis einer eventuellen Systemanalyse sind dabei Kombinationen möglich die beispielsweise vom gezielten Verlegen von Streumunition über den Abschuß panzerfaustähnlicher Flugkörper bis zu einfachen Bahnkorrekturvorrichtungen für die Tochterflugkörper reichen. Aber selbst echt endphasengelenkte Tochterflugkörper können nach dem erfindungsgemäßen Verfahren verteilt werden, wenn sich dies trotz des Aufwandes im Hinblick auf die angestrebte Treffwahrscheinlichkeit ais vorteilhaft erweist. Beim « gezielten » Verlegen von Streumunition wird der Streubereich nicht vor dem Abschuß des Trägerflugkörpers fest vorbestimmt, sondern von der zentralen Such-und Auswerteeinrichtung autonom festgelegt.In the method according to the invention, the demands on the daughter missiles are comparatively low. The child missiles or child projectiles are therefore preferably unguided. As a daughter missile z. B. cluster munitions such as mines, bomblets or the like. Bullet-like bodies, combat bodies with additional drive, etc. are used. Depending on. The task and the result of a possible system analysis are possible combinations that range, for example, from the targeted laying of cluster munitions and the launching of armored fighter-like missiles to simple orbit correction devices for the daughter missiles. But even daughter missiles that are directed to the final phase can be distributed using the method according to the invention, if this proves to be advantageous despite the effort in terms of the target probability. In the case of "targeted" laying of cluster munitions, the range of spread is not fixedly predetermined before the launch vehicle is fired, but is instead determined autonomously by the central search and evaluation device.

Allen Variationen gemeinsam ist das Erreichen einer optimalen Start- oder Abschußposition für die Tochterflugkörper durch Verwendung nur einer zentralen Sensor-Auswerte-Einheit, die dadurch entsprechend hoch entwickelt sein kann. Ein weiterer Vorteil ist darin zu sehen, daß die Erhöhung beim Abschuß des Trägerflugkörpers im Hinblick auf das Überfliegen von Hindernissen vergleichsweise groß sein kann, ohne daß wie bei ungelenkten Flugkörpern durch Windeinflüsse die Schußgenauigkeit darunter leidet. Als Vorteil erweist sich ferner die hohe Flexibilität dervorgenannten Systeme, weil Anzahl und Entwicklungsgrad der Tochterflugkörper nachträglich einfach variiert werden können. Die Kosteneffektivität kann gesteigert, das Entwicklungsrisiko und die Entwicklungszeit können vermindert werden durch die weitgehende Nutzung der einfachen Technologie ungelenkter Flugkörper. Mit dem erfindungsgemäßen Verfahren ist es in sehr einfacher Weise möglich, die bisherigen Schwierigkeiten bei der Aufklärung und Bekämpfung beweglicher gepanzerter Ziele zu überwinden. Diese Schwierigkeiten waren darin begründet, daß einerseits die Ziele sich relativ schnell bewegen, was bedeutet, daß die Zeit zwischen Aufklärung und Bekämpfung minimiert werden muß, und andererseits in der Regel nur ein direkter Treffer des Ziels zum Erfolg führt.Common to all variations is the achievement of an optimal launch or launch position for the daughter missiles by using only a central sensor evaluation unit, which can be correspondingly highly developed. Another advantage can be seen in the fact that the increase in the launching of the carrier missile can be comparatively large with a view to flying over obstacles without the shooting accuracy being affected by wind influences, as in the case of unguided missiles. Another advantage is the high flexibility of the above-mentioned systems, because the number and level of development of the daughter missiles can easily be varied subsequently. The cost effectiveness can be increased, the development risk and the development time can be reduced by the extensive use of the simple technology of guided missiles. With the method according to the invention, it is possible in a very simple manner to overcome the previous difficulties in the reconnaissance and combat of movable armored targets. These difficulties were due to the fact that, on the one hand, the targets move relatively quickly, which means that the time between reconnaissance and combat must be minimized, and on the other hand, only a direct hit of the target usually leads to success.

Das erfindungsgemäße Verfahren wird in der Zeichnung anhand schematischer Darstellungen noch näher erläutert. Es zeigen

  • Figur 1 eine Darstellung möglicher Flugbahnen,
  • Figur 2 eine erfindungsgemäße Anordnung von Verteileinheit und Sucheinrichtung über dem Zielbereich,
  • Figur 3 eine Verteileinheit mit um ihren Schwerpunkt schwenkbaren Abschußrohren und
  • Figur 4 eine Verteileinheit mit Bahnkurve eines Tochterflugkörpers.
The method according to the invention is explained in more detail in the drawing using schematic representations. Show it
  • FIG. 1 shows a representation of possible trajectories,
  • FIG. 2 shows an arrangement according to the invention of the distribution unit and search device above the target area,
  • Figure 3 shows a distribution unit with launch tubes pivotable about their center of gravity and
  • Figure 4 shows a distribution unit with a trajectory of a daughter missile.

Gemäß Fig. 1 wird der nicht gezeigte Trägerflugkörper, vorzugsweise eine ungelenkte Rakete, mittels der Abschußeinrichtung 1 unter der Erhöhung 60 abgeschossen und bewegt sich auf der Bahn A. Werden die zu bekämpfenden Ziele aufgrund vorhergehender Aufklärung im Zielbereich Z angenommen, so wird in bekannter Weise aufgrund entsprechender Dateneingabe vor dem Abschuß der die Verteileinheit enthaltende Kopf an dem Punkt I vom restlichen Trägerflugkörper getrennt und beispielsweise mittels eines Fallschirms oder Bremsklappen bis zum Punkt 11 verzögert, an dem die Bahngeschwindigkeit ausreichend reduziert und die Bahnneigung der Vertikalen so nahe ist, daß entsprechend der DE-A-21 53 994 die Abschußrohre der Verteileinheit abgespreizt werden können.1, the carrier missile, not shown, preferably an unguided rocket, is launched by means of the launcher 1 below the elevation 6 0 and moves on the orbit A. If the targets to be combated are assumed in the target area Z due to previous reconnaissance, it is known in Due to appropriate data input prior to launch, the head containing the distribution unit was separated from the rest of the carrier missile at point I and delayed, for example by means of a parachute or brake flaps, to point 11, at which the path speed was reduced sufficiently and the path inclination was so close to the vertical that accordingly DE-A-21 53 994 the launch tubes of the distribution unit can be spread apart.

Nach dem erfindungsgemäßen Verfahren wird frühestens am Punkt I die in Fig. 2 nur noch gestrichelt angedeutete Ogive 2 des Kopfes bzw. der Verteileinheit 3 mit Bremsfallschirm 4 abgetrennt, so daß der fest mit der Verteileinheit verbundene Suchkopf 5 bereits aus großer Höhe einen entsprechend großen Zielbereich Z erfassen kann. Bevorzugt wird dann über einen dem Suchkopf 5 nachgeschalteten Rechner die im Rahmen der aeroballistischen Möglichkeiten optimale Abstiegsbahn der Verteileinheit 3 berechnet, die durch einen Gleitschirm oder andere entsprechend einstellbare asymmetrische aerodynamische Flächen erreicht werden kann.According to the method of the invention, at the earliest at point I, the ogive 2 of the head or the distribution unit 3, which is only indicated by dashed lines in FIG. 2, is separated with a brake parachute 4, so that the search head 5, which is firmly connected to the distribution unit, already has a correspondingly large target area from a great height Z can capture. The descent path of the distribution unit 3, which is optimal within the scope of the aeroballistic possibilities and which can be achieved by means of a paraglider or other correspondingly adjustable asymmetrical aerodynamic surfaces, is then preferably calculated via a computer connected to the search head 5.

Im Verlaufe des weiteren Abstiegs der Verteileinheit 3 vom Punkt II zum Punkt 111 in Fig. 1 werden die Abschußrohre 6 mit je einem darin befindlichen Tochtergeschoß abgespreizt wodurch sich die Geschwindigkeit der Verteileinheit weiter reduziert. Im Punkt III hat die Verteileinheit 3 die in Fig.2 gezeigte Konfiguration K und befindet sich in der Höhe h über dem Zielbereich Z. Ab dieser Höhe können aufgrund des im Rechner gespeicherten aeroballistischen Verhaltens der Tochtergeschosse zunächst die Ziele am äußeren Rand des' Zielbereiches durch Wahl eines geeigneten Abschußzeitpunktes bekämpft werden. Da der Zielbereich eine Fläche ist, können durch eine geringe Rotation der Verteileinheit um ihre Längsachse 7 alle äußeren Zeile erfaßt werden. Das dazu notwendige Drehmo- . ment um die Längsachse wird bevorzugt aerodynamisch, z. B. durch den Fallschirm 4, erzeugt. Die weiter im Zentrum des Zielbereiches Z liegenden Ziele können bekämpft werden, wenn der Gefechtskopf weiter abgesunken ist.In the course of the further descent of the distribution unit 3 from point II to point 111 in FIG. 1, the launch tubes 6, each with a subsidiary floor located therein, are spread apart, which further reduces the speed of the distribution unit. At point III, the distribution unit 3 has the configuration K shown in FIG. 2 and is located at a height h above the target area Z. From this height, the targets on the outer edge of the ' target area can first be passed due to the aeroballistic behavior of the subsidiary storeys stored in the computer The choice of a suitable time for shooting. Since the target area is a surface, all outer lines can be detected by a slight rotation of the distribution unit about its longitudinal axis 7. The necessary torque. ment about the longitudinal axis is preferably aerodynamically, for. B. generated by the parachute 4. The targets further in the center of the target area Z can be fought if the warhead has sunk further.

Wird ein hochentwickelter Suchkopf 5 verwendet, der bereits in der Startphase des Trägerflugkörpers arbeitet, so kann abweichend vom Vorstehenden die Auslösung der Vorgänge am Punkt I autonom durch die Sucheinrichtung bei Lokalisierung des Zielbereiches Z erfolgen. Diese Ermittlung der Zielkoordinaten erst kurz vor der Bekämpfung ist insbesondere bei schnell beweglichen Zielen von Vorteil, weil - wie in Fig. 1 gezeigt - auf der gleichen Primärflugbahn A je nach den Auslösepunkten I oder I' und 11 oder II' unterschiedliche Zielbereiche Z oder Z' erfaßt werden können. Im Punkt III' befindet sich der Gefechtskopf wieder in Höhe h über dem Zielbereich Z', ab welcher die Bekämpfung der Ziele gemäß Fig. 2 erfolgen kann.If a highly developed search head 5 is used, which is already working in the launch phase of the carrier missile, then, in deviation from the above, the processes at point I can be triggered autonomously by the search device when the target area Z is located. This determination of the target coordinates only shortly before the combat is particularly advantageous in the case of targets that move quickly because - as shown in FIG. 1 - different target areas Z or Z on the same primary trajectory A, depending on the trigger points I or I 'and 11 or II' 'can be recorded. At point III ', the warhead is again at a height h above the target area Z', from which the targets according to FIG. 2 can be combated.

In Fig. 3 ist eine Verteileinheit 3 mit Bremsfallschirm 4 und Such-Auswerte-Einrichtung 5 gezeigt, deren Abschußrohre 6 um ihren Schwerpunkt S und den der Verteileinheit 3 schwenkbar sind. Zur Vereinfachung der zeichnerischen Darstellung sind nur zwei dicht hintereinander angeordnete Abschußrohre 6 in ihrer ausgestellten Position gezeigt.FIG. 3 shows a distribution unit 3 with a brake parachute 4 and a search evaluation device 5, the launch tubes 6 of which can be pivoted about their center of gravity S and that of the distribution unit 3. To simplify the drawing, only two launch tubes 6 arranged closely one behind the other are shown in their extended position.

Sofern auch die Tochterflugkörper innerhalb der Abschußrohre so angeordnet sind, daß auch ihr Schwerpunkt mit dem der Verteileinheit in der Zeichenebene zusammenfällt, kommt es beim Abschuß eines Tochterflugkörpers zu keiner Verschiebung des Schwerpunktes in Richtung der Längsachse 7. Die durch die Hintereinanderanordnung der Abschußrohre 6 bedingte Schwerpunktsverschiebung senkrecht zur Zeichenebene ist gering, so daß durch Massen- änderungen bedingte Pendelbewegungen der Verteileinheit 3 weitgehend ausgeschaltet sind.If the daughter missiles are also arranged within the launch tubes so that their center of gravity coincides with that of the distribution unit in the drawing plane, there is no ver when a daughter missile is launched shift of the center of gravity in the direction of the longitudinal axis 7. The shift in the center of gravity due to the arrangement of the launch tubes 6 one behind the other is small, so that pendulum movements of the distribution unit 3 due to mass changes are largely eliminated.

Die Tochterflugkörper können mit einfachen Korrekturvorrichtungen für ihre Flugbahn versehen werden. Gemäß Fig. 4 kann dann eine Verteileinheit 3 mit nur wenig oder sogar nicht nach außen abgespreizten Abschußrohren 6 verwendet werden, wodurch in vorteilhafter Weise die nach einem Abschuß auftretende seitliche Schwerpunktsverschiebung kleingehalten wird. Die Tochterflugkörper können mit ausklappbaren angestellten Rudern (Steuerflächen) versehen sein, so daß sie sich auf der Flugbahn B bewegen, während die Verteileinheit 3 sich auf der senkrechten Abstiegsbahn C bewegt. Die Trennung vom Rohr 4 und das Durchfliegen der Bahn B kann alleine durch das Gewicht oder ergänzt durch einen Antrieb erfolgen. Der zur Bekämpfung der Ziele notwendige seitliche Abstand der Tochterflugkörper auf der Bahn B von der senkrechten Bahn C der Verteileinheit 3 kann wie in Fig.2 durch die Ausstoßhöhe und/oder durch Variation des Rudereinstellwinkels erreicht werden.The daughter missiles can be provided with simple correction devices for their trajectory. According to FIG. 4, a distribution unit 3 can then be used with launch tubes 6 that are only slightly or even not spread outwards, whereby the lateral shift in the center of gravity that occurs after a launch is advantageously kept small. The daughter missiles can be provided with fold-out oars (control surfaces) so that they move on the trajectory B, while the distribution unit 3 moves on the vertical descent path C. The separation from the tube 4 and flying through the web B can be done solely by the weight or supplemented by a drive. The lateral distance of the daughter missiles on orbit B from the vertical orbit C of distribution unit 3, which is necessary to combat the targets, can be achieved, as in FIG. 2, by the ejection height and / or by varying the rudder setting angle.

Claims (6)

1. Process for the distribution of ammunition in which a carrier flight body, or a distribution unit (3) associated therewith, before the ammunition formed as two or more sub-flight bodies is retarded before the releasing of the sub-flight bodies by additional braking means (4) and is conveyed in a predetermined release position, characterised in that the release of the sub-flight bodies is, at the time, controlled centrally for each on its own by means of a searching arrangement (5) assigned to the distribution unit (3) common to all sub-flight bodies, with coupled plotting arrangement dependent on the target determination by the searching arrangement (5).
2. Process according to Claim 1, characterised in that furthermore the beginning of the additional retarding of the carrier flight body or of the distribution unit (3) and the release of the preferably provided separation of the distribution unit (3) from the residual carrier flight body are controlled by means of the searching arrangement (5) in accordance with the determination of the target region (Z).
3. Process according to Claim 1 or 2, characterised in that, after the determination of the target region (Z) through the searching arrangement (5) by means of its plotting arrangement, the optimal descent path of the carrier flight body or of the distribution unit (3) are determined and caused to undergo the corresponding path corrections.
4. Process according to one of Claims 1 to 3, characterised in that, for delaying the multiple combating of a target, the target coordinates of a released sub-flight body are accumulated in the plotting arrangement and are blocked for the remaining sub-flight bodies of the distribution unit (3).
5. Process according to one of Claims 1 to-4, characterised in that, for the release of the sub-flight bodies, use is made of the principle of rocket propulsion or of the Davis cannon with a compensation mass dischargeable opposite to the sub-flight body.
6. Process according to one of Claims 1 to 5, characterised in that that sub-flight bodies are released from discharge tubes (6) by launching rails or the like, which observed in a lateral view of the distribution unit (3) are formed rotatably about the centre gravity (S) of the distribution unit (3) and so are arranged in or on the sub-flight bodies thereof, that the centre gravity thereof observed in the same lateral view coincides with that of the distribution unit (3) at least approximately, so that, by the release of the sub-flight bodies, practically no change in the position of the centre of gravity of the distribution unit (3) in its length direction takes place.
EP81107358A 1980-10-10 1981-09-17 Method for the distribution of ammunition Expired EP0049778B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19803038295 DE3038295A1 (en) 1980-10-10 1980-10-10 METHOD FOR DISTRIBUTING COMBAT BODIES
DE3038295 1980-10-10

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EP0049778A1 EP0049778A1 (en) 1982-04-21
EP0049778B1 true EP0049778B1 (en) 1985-01-30

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2534370B1 (en) * 1982-10-11 1986-12-19 Luchaire Sa DEVICE INTENDED FOR ATTACKING OVER OBJECTIVES SUCH AS ESPECIALLY ARMORED
DE3319824A1 (en) * 1983-06-01 1984-12-06 Diehl GmbH & Co, 8500 Nürnberg METHOD FOR COMBATING TARGET OBJECTS BY MEANS OF BOMBLETS AND BOMBLET CARRIER BODIES FOR EXERCISING THE METHOD
GB2392227A (en) * 2002-08-20 2004-02-25 Eric Robinson Warhead

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Publication number Priority date Publication date Assignee Title
US3216321A (en) * 1964-01-07 1965-11-09 Fay E Null Multi-ring dart warhead
DE2032126C3 (en) * 1970-06-30 1980-08-28 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Lock system for waters
FR2144917A5 (en) * 1971-07-02 1973-02-16 Serat
BE790638A (en) * 1971-10-29 1973-02-15 Dynamit Nobel Ag EJECTION HEAD, IN PARTICULAR FOR ROCKETS
FR2204294A5 (en) * 1972-10-25 1974-05-17 Cnim
DE2347374C2 (en) * 1973-09-20 1982-05-13 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Distance fuse for a warhead
DE2532479C3 (en) * 1975-07-19 1980-11-27 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Method for combating earth targets by means of a remotely steerable aircraft equipped for air reconnaissance and another remotely steerable aircraft equipped with weapons as well as two stationary transmitting stations

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EP0049778A1 (en) 1982-04-21
DE3168645D1 (en) 1985-03-14

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