EP0277445B1 - Carrier projectile with submissiles for creating a predetermined ground-striking pattern - Google Patents

Carrier projectile with submissiles for creating a predetermined ground-striking pattern Download PDF

Info

Publication number
EP0277445B1
EP0277445B1 EP87402969A EP87402969A EP0277445B1 EP 0277445 B1 EP0277445 B1 EP 0277445B1 EP 87402969 A EP87402969 A EP 87402969A EP 87402969 A EP87402969 A EP 87402969A EP 0277445 B1 EP0277445 B1 EP 0277445B1
Authority
EP
European Patent Office
Prior art keywords
projectiles
sub
projectile
trajectory
zone
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP87402969A
Other languages
German (de)
French (fr)
Other versions
EP0277445A1 (en
Inventor
Gérard Dieval
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0277445A1 publication Critical patent/EP0277445A1/en
Application granted granted Critical
Publication of EP0277445B1 publication Critical patent/EP0277445B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile

Definitions

  • the present invention relates to a projectile forming the head of a vector, such as a missile, such a vector possibly comprising a propellant and being provided with a tail or a piloting system, so as to have a defined ballistic trajectory. .
  • the present invention relates to a projectile comprising sub-projectiles, ejected at a given time on the trajectory of the carrier projectile and corresponding to a predefined impact area.
  • main projectile carrying sub-projectiles (or sub-charges) to be distributed over large surfaces or volumes.
  • the object of the present invention is to maximize the ratio of sub-projectiles to goal on lost sub-projectiles, it being understood that sub-projectiles at target are sub-projectiles arriving under suitable conditions of speed and attitude in an area. predefined target.
  • the arrangement of sub-projectiles in the main projectile is arranged so as to obtain, during ejection, a spray of sub-projectiles of predefined shape, adapted to the shape of the target area.
  • the subject of the invention is a projectile as defined by claim 1.
  • FIG. 1a is therefore a diagram illustrating the relationship between sub-projectiles at target and lost sub-projectiles.
  • the trajectory of a main projectile has been shown at T relative to the ground S for example, up to a point A which is the point of ejection (or release) of the sub-projectiles. From this point A, the sub-projectiles are conventionally ejected into a spray 12 whose general shape recalls that of a cone, modified by the effect of gravity; the intersection of this sheaf 12 with the ground S is a surface 13 called impact zone, shown by way of example in FIG. 1 b, seen from above.
  • the impact zone 13 would of course be circular. It deforms until it becomes a substantially parabolic open curve when the angle of the path T with the ground decreases, that is to say when the flight of the main projectile is more horizontal. As is known, modern projectiles tend to fly as close to the ground as possible and therefore the angle of the spray 12 with the ground is generally very small.
  • FIG. 1b shows a grid Z, a so-called efficiency zone, the shape of which is predefined, for example here a square, and in which it is desired that the effectiveness of the sub-projectiles is maximum, that is to say -to say that their speed and attitude are suitable for destroying a target there. It appears that if the efficiency zone has a shape whose maximum width is of the order of magnitude of the maximum length, the impact zone 13 is much larger than the zone Z, especially in the case where the trajectory of the main projectile is fairly grazing.
  • the velocities and densities of the sub-projectiles are not homogeneous in the impact zone 13, even in the case where precautions are taken to preserve the sub-projectiles, after ejection, the initial trajectory of the projectile main and their attitude on this trajectory.
  • the part (13a) of the zone 13 which is closest to the ejection point (A) is much more dense in sub-projectile impacts than the part (13b) which is the most distant therefrom; in addition, the speed of the sub-projectiles in the part 13a is higher than it can be in the part 13b. This results in a decrease in the effectiveness of the sub-projectiles as one moves away from the point of ejection.
  • the efficiency zone Z must therefore not only be entirely covered by the impact zone 13 but also must preferably be located in the part 13a of this zone 13.
  • FIG. 1a There is shown in Figure 1a by an ellipse 10, in dotted lines, a cross section made in the sheaf 12 before the impact thereof on the ground and there is shown by a gridded area 11 the part of the sheaf 12 which corresponds to the sub-projectiles whose impact will be in zone Z.
  • the sub-projectiles contained in the spray outside zone 11 will not reach the zone of effectiveness Z.
  • the sub-projectiles are placed in the main projectile as a function of the shape of the desired efficiency zone Z, as shown in FIG. 2.
  • Figure 2 there is shown in cross section the envelope 3 of the main projectile and, inside, by way of example a rectangle 50 in dotted lines representing the loading of sub-projectiles in the main projectile.
  • the shape given to the loading of sub-projectiles is a function in particular of the shape desired for the efficiency zone Z and of the angle which the trajectory of the main projectile makes with the ground.
  • a rectangular loading such as 50 in FIG. 2 can correspond to a rectangular or square zone Z, depending on the angle of incidence of the trajectory.
  • the main projectile has a system giving it an angular reference, for example the vertical, and a telemetry system so that the ejection point (A) is located at a known distance from the impact zone.
  • means 80 are also shown for wedging the assembly 50 in the casing 3.
  • the main projectile will only carry the sub-projectiles which will have an impact effectively in the predefined efficiency zone Z, thus allowing a gain in space in the main projectile and a gain in weight and, thereby even, to be able to target with a single main projectile larger Z zones.
  • the spaces (marked 30) left free in the envelope 3 can for example be used to have the electronic equipment necessary for the main projectile.
  • FIG. 3a represents an embodiment of the projectile according to the invention, seen diagrammatically in longitudinal section.
  • This projectile with a longitudinal axis XX, is generally identified 1 and consists of a cylindrical casing 3, ending on one side with a warhead 2 of aerodynamic shape, for example substantially conical; at the other end, the projectile is fixed on the rest of the vector, represented by dotted lines 30.
  • sub-projectiles 5 Inside the envelope 3 are longitudinally disposed sub-projectiles 5. Each of them consists of a cylindrical body 54 terminating forwards by an aerodynamic head 55, for example substantially conical, and of the 'other side by a tail 56, allowing it to maintain a given attitude on a given trajectory.
  • the sub-projectiles 5 are arranged in the projectile according to the transverse arrangement illustrated in FIG. 2 and, longitudinally along one or, as in the case of FIG. 3a, several rows, marked 71, 72 and 73. They are arranged there with a single orientation, namely their head 55 directed towards the front of the projectile.
  • Sub-projectiles can be of the explosive ammunition, fireworks (infrared or illuminating) type, lure or kinetic energy munition.
  • FIG. 4 is a cross-sectional view of one half of the projectile 1 of FIG. 3a, at the level of the tail of the sub-projectiles of one of the rows 71, 72 or 73.
  • the outer casing 3 is illustrated and, towards the center, an axis 20 supporting the warhead 2 and an inner casing 31.
  • the axis 20 of the warhead is movable in the casing 31 to allow the ejection of the warhead, as described below. All of the sub-projectiles 5 are disposed between the envelopes 3 and 31.
  • the central part (inside of the casing 31) of the projectile does not include sub-projectiles.
  • the transverse dimensions of the envelope 31 are small enough so that this does not translate, at the level of the zone Z (FIG. 1), by an annoying gap.
  • FIG. 4 also shows the body 54 of each of the sub-projectiles 5 and their tail unit 56, the elements 54 and 56 being hatched for the clarity of the drawing.
  • the tail of each sub-projectile 5 consists of three fins, arranged at 120 ° .
  • the bodies 54 of the sub-projectiles are arranged in a hexagon, an example of which is shown in dotted lines 74, the center of the bodies 54 forming the vertices of the hexagon and the bodies 54 being tangent to each other.
  • the fins are arranged one inside the other so that the structure formed by all of the sub-projectiles is self-locking, that is to say that in the center of hexagon 74 there are six fins belonging respectively to the six sub-projectiles 5 of the hexagon, blocked one inside the other.
  • wedging elements 82 between the sub-projectiles 5, at the level of the bodies 54.
  • These elements 82 are for example of substantially cylindrical shape and extend over the entire length of the bodies 54, or only on part of them. For the clarity of FIG. 2, the surface of the elements 82 is dotted.
  • These internal wedging elements 82 have the function of improving the rigidity of all of the sub-projectiles 5, in particular in the case where the projectile is rotated around its longitudinal axis.
  • the wedging elements 82 are made of a flexible material, such as plastic foam, pre-stressed so as to make it possible to make up for any play in the structure.
  • truncated wedging elements marked 83, again with the aim of improving the rigidity of the structure.
  • these elements 81 have a shape adapted to the free space between the structure formed by the sub-projectiles and the outer envelope 3. They are not necessarily of constant section. They are for example made of a plastic material and are preferably made of a relatively rigid material and capable of breaking up during the ejection of the sub-projectiles, according to a mechanism described below, so as not to disturb this ejection.
  • the means for wedging the load of sub-projectiles also include wedging elements 84, similar to the elements 81, intended to contain the load and leave the space 30 free.
  • the volumes left free between the walls 31 and 3, the sub-projectiles 5 and the wedging elements 81, 82, 83 or 84 are filled with a powder material 9 whose function is, on the one hand, to '' improve the immobilization of the sub-projectiles 5 in the envelope 3 and, on the other hand, to ensure a separation between each of the rows 71, 72 and 73 ( Figure 3a) for a reason related to the ejection of the sub -projectiles, as set out below.
  • This powder 9 also makes it possible to view the point of ejection of the sub-projectiles, which facilitates its use.
  • the main projectile 1 (FIG. 3a) also includes a disc 6 closing the space between the envelopes 3 and 31 at the rear of the loading of sub-projectiles, this disc 6 actuated by propulsion means 4 during the ejection of the sub-projectiles.
  • FIGS. 3b and 3c are diagrams illustrating the mechanism for ejecting the sub-projectiles 5 from the main projectile 1.
  • a first step under the action of the propulsion means 4 shown diagrammatically at the rear of the projectile 1, the axis 20 of the warhead 2 slides inside the casing 31 until the warhead separates from the projectile. This is designed so that it then remains stable and does not interfere with the movement of the sub-projectiles being ejected or that of the main projectile.
  • the propulsion means 4 impart a relative forward movement to the disc 6 relative to the casing 3, leading to the successive ejection of the rows 71, 72 and 73 of sub-projectiles 5.
  • the wedging elements 81-84 and the pulverulent material 9 separate from the sub-projectiles as they appear at the edge of the envelope 3.
  • each of the sub-projectiles 5 is animated at its exit from the envelope 3, in addition to a relative longitudinal speed, a radial speed often called expansion speed, due to the aerodynamic force which is exerted on them at the exit of the envelope 3 and, if necessary, at the rotation on itself of the main projectile. Furthermore, each of the rows is, when it leaves, slowed down by this aerodynamic force. The two phenomena combined make it possible to obtain an interpenetration of the different rows, as shown in FIG. 3c where the three rows being fully ejected, the different sub-projectiles 5 are found substantially on the same line 74 to form a single sheaf, animated by 'a longitudinal speed and a radial speed of expansion.
  • the radial speed of expansion is controllable, which allows, with the choice of the shape of the loading of sub-projectiles, to adapt the shape of the spray to that of the desired efficiency zone.
  • This speed of expansion depends on the speed of rotation of the main projectile 1, the dimensioning of the setting elements, the geometric characteristics of the sub-projectiles and their position relative to the longitudinal axis (XX) of the main projectile.
  • the sub-projectiles are rigidly held in place before ejection so as, at the time of ejection, to be able to follow the planned trajectory.
  • means are provided so that, during this ejection, the trajectory of each of the sub-projectiles is neither disturbed by the various constituents of the main projectile, nor by the other sub-projectiles.
  • the main projectile has been described as having a cylindrical body with a circular section, but this section can have other shapes, for example square, the sub-projectiles then being provided with four fins. More generally, other geometric shapes can be used for the body of the projectile, the body and the tail of the sub-projectiles and their organization (in hexagon in FIG. 4), provided that the bodies of the sub-projectiles are tangent and their tailplane organized in a self-locking manner.
  • Air-Sol or Sol-Sol vector type has been described.
  • Other applications are of course possible such as those where the target area is at sea or in the air (anti-helicopter vector for example).

Description

La présente invention concerne un projectile formant la tête d'un vecteur, tel qu'un missile, un tel vecteur comportant éventuellement un propulseur et étant muni d'un empennage ou d'un système de pilotage, de sorte à avoir une trajectoire balistique définie.The present invention relates to a projectile forming the head of a vector, such as a missile, such a vector possibly comprising a propellant and being provided with a tail or a piloting system, so as to have a defined ballistic trajectory. .

Plus précisément, la présente invention se rapporte à un projectile comportant des sous-projectiles, éjectés à un instant donné sur la trajectoire du projectile porteur et correspondant à une zone d'impact prédéfinie.More specifically, the present invention relates to a projectile comprising sub-projectiles, ejected at a given time on the trajectory of the carrier projectile and corresponding to a predefined impact area.

Les systèmes d'armes modernes utilisent très souvent le concept de projectile, appelé projectile principal, transportant des sous-projectiles (ou sous-charges) devant être répartis sur des surfaces ou des volumes importants.Modern weapon systems very often use the concept of projectile, called main projectile, carrying sub-projectiles (or sub-charges) to be distributed over large surfaces or volumes.

Dans les systèmes connus, il n'est pas habituellement pris de précautions particulières pour l'organisation des sous-projectiles à l'intérieur du projectile principal. Cela se traduit par une répartition et une orientation aléatoires des sous-projectiles lors du largage ou, au moins, un manque sensible de précision sur la vitesse et l'attitude des sous-projectiles. Le résultat en est que seule une portion, qui est parfois faible, des sous-projectiles arrive à atteindre la zone où se trouve la cible, dans des conditions correctes. De plus, une zone cible de forme prédéfinie doit être arrosée très largement pour être effectivement couverte, ceci étant dû à des considérations géométriques développées plus loin. En conséquence, une partie importante des sous-projectiles est perdue ce qui, pour une efficacité donnée, revient à une perte de poids et de place dans le projectile principal.In known systems, special precautions are not usually taken for the organization of the sub-projectiles inside the main projectile. This results in a random distribution and orientation of the sub-projectiles during the dropping or, at least, a noticeable lack of precision on the speed and attitude of the sub-projectiles. The result is that only a portion, which is sometimes small, of the sub-projectiles succeeds in reaching the zone where the target is, under correct conditions. In addition, a target area of predefined shape must be watered very widely to be effectively covered, this being due to geometric considerations developed later. Consequently, a significant part of the sub-projectiles is lost which, for a given efficiency, amounts to a loss of weight and of space in the main projectile.

La présente invention a pour but de maximiser le rapport sous-projectiles au but sur sous-projectiles perdus, étant entendu qu'on appelle sous-projectiles au but les sous-projectiles arrivant dans des conditions convenables de vitesse et d'attitude dans une zone cible prédéfinie.The object of the present invention is to maximize the ratio of sub-projectiles to goal on lost sub-projectiles, it being understood that sub-projectiles at target are sub-projectiles arriving under suitable conditions of speed and attitude in an area. predefined target.

A cet effet, la disposition des sous-projectiles dans le projectile principal est aménagée de sorte à obtenir, lors de l'éjection, une gerbe de sous-projectiles de forme prédéfinie, adaptée à la forme de la zone cible.For this purpose, the arrangement of sub-projectiles in the main projectile is arranged so as to obtain, during ejection, a spray of sub-projectiles of predefined shape, adapted to the shape of the target area.

Plus précisément, l'invention a pour objet un projectile tel que défini par la revendication 1.More specifically, the subject of the invention is a projectile as defined by claim 1.

D'autres objets, particularités et résultats de l'invention ressortiront de la description suivante, illustrée par les dessins annexés qui représentent:

  • - les figures 1, a et b, des schémas explicatifs ;
  • - la figure 2, le schéma de la disposition des sous-projectiles selon l'invention ;
  • - les figures 3, a à c, un mode de réalisation du projectile selon l'invention et son fonctionnement ;
  • - la figure 4, un mode de réalisation de la disposition des sous-projectiles selon l'invention.
Other objects, features and results of the invention will emerge from the following description, illustrated by the appended drawings which represent:
  • - Figures 1, a and b, explanatory diagrams;
  • - Figure 2, the diagram of the arrangement of sub-projectiles according to the invention;
  • - Figures 3, a to c, an embodiment of the projectile according to the invention and its operation;
  • - Figure 4, an embodiment of the arrangement of sub-projectiles according to the invention.

Sur ces différentes figures, les mêmes références se rapportent aux mêmes éléments.In these different figures, the same references relate to the same elements.

La figure 1a est donc un schéma illustrant le rapport sous-projectiles au but sur sous-projectiles perdus.FIG. 1a is therefore a diagram illustrating the relationship between sub-projectiles at target and lost sub-projectiles.

On a représenté en T la trajectoire d'un projectile principal par rapport au sol S par exemple, jusqu'en un point A qui est le point d'éjection (ou de largage) des sous-projectiles. A partir de ce point A , les sous-projectiles sont classiquement éjectés en une gerbe 12 dont la forme générale rappelle celle d'un cône, modifié par l'effet de la pesanteur ; l'intersection de cette gerbe 12 avec le sol S est une surface 13 appelée zone d'impact, représentée à titre d'exemple sur la figure 1 b, vue de dessus.The trajectory of a main projectile has been shown at T relative to the ground S for example, up to a point A which is the point of ejection (or release) of the sub-projectiles. From this point A, the sub-projectiles are conventionally ejected into a spray 12 whose general shape recalls that of a cone, modified by the effect of gravity; the intersection of this sheaf 12 with the ground S is a surface 13 called impact zone, shown by way of example in FIG. 1 b, seen from above.

Sur la figure 1 b, on a tracé à titre de référence en traits pointillés le prolongement de la trajectoire T du projectile principal.In FIG. 1 b, the extension of the trajectory T of the main projectile has been drawn by reference with dotted lines.

Si la trajectoire T était verticale, la zone d'impact 13 serait bien entendu circulaire. Elle se déforme jusqu'à devenir une courbe ouverte sensiblement parabolique lorsque l'angle de la trajectoire T avec le sol diminue, c'est-à-dire lorsque le vol du projectile principal est plus horizontal. Ainsi qu'il est connu, les projectiles modernes tendent à avoir un vol aussi près du sol que possible et donc l'angle de la gerbe 12 avec le sol est en général très faible.If the trajectory T were vertical, the impact zone 13 would of course be circular. It deforms until it becomes a substantially parabolic open curve when the angle of the path T with the ground decreases, that is to say when the flight of the main projectile is more horizontal. As is known, modern projectiles tend to fly as close to the ground as possible and therefore the angle of the spray 12 with the ground is generally very small.

On a représenté en quadrillé sur la figure 1 b une zone Z dite zone d'efficacité dont la forme est prédéfinie, par exemple ici un carré, et dans lequel on souhaite que l'efficacité des sous-projectiles soit maximum c'est-à-dire que leur vitesse et leur attitude soit convenables pour y détruire une cible. Il apparaît que si la zone d'efficacité a une forme dont la largeur maximale est de l'ordre de grandeur de la longueur maximale, la zone d'impact 13 se trouve beaucoup plus grande que la zone Z, surtout dans le cas où la trajectoire du projectile principal est assez rasante.FIG. 1b shows a grid Z, a so-called efficiency zone, the shape of which is predefined, for example here a square, and in which it is desired that the effectiveness of the sub-projectiles is maximum, that is to say -to say that their speed and attitude are suitable for destroying a target there. It appears that if the efficiency zone has a shape whose maximum width is of the order of magnitude of the maximum length, the impact zone 13 is much larger than the zone Z, especially in the case where the trajectory of the main projectile is fairly grazing.

En outre, les vitesses et les densités des sous-projectiles ne sont pas homogènes dans la zone d'impact 13, même dans le cas où des précautions sont prises pour conserver aux sous-projectiles, après l'éjection, la trajectoire initiale du projectile principal et leur attitude sur cette trajectoire. En effet, la partie (13a) de la zone 13 qui est la plus près du point d'éjection (A) est beaucoup plus dense en impacts de sous-projectiles que la partie (13b) qui en est la plus éloignée ; en outre, la vitesse des sous-projectiles dans la partie 13a est supérieure à ce qu'elle peut être dans la partie 13b. Il en résulte une décroissance de l'efficacité des sous-projectiles au fur et à mesure que l'on s'éloigne du point d'éjection. La zone d'efficacité Z doit donc non seulement être couverte en totalité par la zone d'impact 13 mais en plus doit se situer de préférence dans la partie 13a de cette zone 13 .In addition, the velocities and densities of the sub-projectiles are not homogeneous in the impact zone 13, even in the case where precautions are taken to preserve the sub-projectiles, after ejection, the initial trajectory of the projectile main and their attitude on this trajectory. Indeed, the part (13a) of the zone 13 which is closest to the ejection point (A) is much more dense in sub-projectile impacts than the part (13b) which is the most distant therefrom; in addition, the speed of the sub-projectiles in the part 13a is higher than it can be in the part 13b. This results in a decrease in the effectiveness of the sub-projectiles as one moves away from the point of ejection. The efficiency zone Z must therefore not only be entirely covered by the impact zone 13 but also must preferably be located in the part 13a of this zone 13.

On a représenté sur la figure 1a par une ellipse 10, en traits pointillés, une coupe transversale pratiquée dans la gerbe 12 avant l'impact de celle-ci sur le sol et on a représenté par une zone quadrillée 11 la partie de la gerbe 12 qui correspond aux sous-projectiles dont l'impact se fera dans la zone Z. Les sous-projectiles contenus dans la gerbe hors de la zone 11 n'atteindront pas la zone d'efficacité Z.There is shown in Figure 1a by an ellipse 10, in dotted lines, a cross section made in the sheaf 12 before the impact thereof on the ground and there is shown by a gridded area 11 the part of the sheaf 12 which corresponds to the sub-projectiles whose impact will be in zone Z. The sub-projectiles contained in the spray outside zone 11 will not reach the zone of effectiveness Z.

Selon l'invention, on dispose les sous-projectiles dans le projectile principal en fonction de la forme de la zone d'efficacité Z souhaitée, ainsi que le montre la figure 2.According to the invention, the sub-projectiles are placed in the main projectile as a function of the shape of the desired efficiency zone Z, as shown in FIG. 2.

En effet, les calculs et expériences de la Déposante ont montré que la section transversale de la gerbe obtenue est fonction de la forme de la section du chargement : sensiblement une homothétie.Indeed, the Depositor's calculations and experiments have shown that the cross section of the sheaf obtained is a function of the shape of the section of the load: substantially a homothety.

Sur la figure 2, on a représenté vue en section transversale l'enveloppe 3 du projectile principal et, à l'intérieur, à titre d'exemple un rectangle 50 en traits pointillés représentant le chargement de sous-projectiles dans le projectile principal.In Figure 2, there is shown in cross section the envelope 3 of the main projectile and, inside, by way of example a rectangle 50 in dotted lines representing the loading of sub-projectiles in the main projectile.

Plus précisément, la forme donnée au chargement de sous-projectiles est fonction notamment de la forme souhaitée pour la zone d'efficacité Z et de l'angle que fait la trajectoire du projectile principal avec le sol. C'est ainsi qu'un chargement rectangulaire tel que 50 sur la figure 2 peut correspondre à une zone Z rectangulaire ou carrèe, selon l'angle d'incidence de la trajectoire.More precisely, the shape given to the loading of sub-projectiles is a function in particular of the shape desired for the efficiency zone Z and of the angle which the trajectory of the main projectile makes with the ground. Thus a rectangular loading such as 50 in FIG. 2 can correspond to a rectangular or square zone Z, depending on the angle of incidence of the trajectory.

La seule condition au fonctionnement de ce dispositif est que le projectile principal dispose d'un système lui donnant une référence angulaire, par exemple la verticale, et d'un système de télémétrie de sorte que le point d'éjection (A) soit situé à une distance connue de la zone d'impact.The only condition for the operation of this device is that the main projectile has a system giving it an angular reference, for example the vertical, and a telemetry system so that the ejection point (A) is located at a known distance from the impact zone.

Sur la figure 2, on a représenté en outre en 80 des moyens de calage de l'ensemble 50 dans l'enveloppe 3.In FIG. 2, means 80 are also shown for wedging the assembly 50 in the casing 3.

Il apparaît ainsi que ne seront emportés par le projectile principal que les sous-projectiles qui auront un impact effectivement dans la zone d'efficacité prédéfinie Z, permettant ainsi un gain d'espace dans le projectile principal et un gain de poids et, par là même, de pouvoir viser avec un seul projectile principal des zones Z plus importantes. Les espaces (repérés 30) laissés libres dans l'enveloppe 3 peuvent être par exemple utilisés pour disposer des équipements électroniques nécessaires au projectile principal.It thus appears that the main projectile will only carry the sub-projectiles which will have an impact effectively in the predefined efficiency zone Z, thus allowing a gain in space in the main projectile and a gain in weight and, thereby even, to be able to target with a single main projectile larger Z zones. The spaces (marked 30) left free in the envelope 3 can for example be used to have the electronic equipment necessary for the main projectile.

La figure 3a représente un mode de réalisation du projectile selon l'invention, vu schématiquement en coupe lqngitudinale.FIG. 3a represents an embodiment of the projectile according to the invention, seen diagrammatically in longitudinal section.

Ce projectile, d'axe longitudinal XX, est repéré globalement 1 et se compose d'une enveloppe 3 cylindrique, se terminant d'un côté par une ogive 2 de forme aérodynamique, par exemple sensiblement conique ; à l'autre extrémité, le projectile vient se fixer sur le reste du vecteur, représenté par des traits pointillés 30.This projectile, with a longitudinal axis XX, is generally identified 1 and consists of a cylindrical casing 3, ending on one side with a warhead 2 of aerodynamic shape, for example substantially conical; at the other end, the projectile is fixed on the rest of the vector, represented by dotted lines 30.

A l'intérieur de l'enveloppe 3 sont disposés longitudinalement des sous-projectiles 5. Chacun d'eux est constitué d'un corps cylindrique 54 se terminant vers l'avant par une tête 55 aérodynamique, par exemple sensiblement conique, et de l'autre côté par un empennage 56, lui permettant de conserver une attitude donnée sur une trajectoire donnée. Les sous-projectiles 5 sont disposés dans le projectile selon l'arrangement transversal illustré figure 2 et, longitudinalement selon une ou, comme dans le cas de la figure 3a, plusieurs rangées, repérées 71, 72 et 73. Ils y sont disposés avec une orientation unique, à savoir leur tête 55 dirigée vers l'avant du projectile.Inside the envelope 3 are longitudinally disposed sub-projectiles 5. Each of them consists of a cylindrical body 54 terminating forwards by an aerodynamic head 55, for example substantially conical, and of the 'other side by a tail 56, allowing it to maintain a given attitude on a given trajectory. The sub-projectiles 5 are arranged in the projectile according to the transverse arrangement illustrated in FIG. 2 and, longitudinally along one or, as in the case of FIG. 3a, several rows, marked 71, 72 and 73. They are arranged there with a single orientation, namely their head 55 directed towards the front of the projectile.

Les sous-projectiles peuvent être du type munition explosive, munition à artifice (infrarouge ou éclairante), leurre ou munition à énergie cinétique .Sub-projectiles can be of the explosive ammunition, fireworks (infrared or illuminating) type, lure or kinetic energy munition.

Un mode de réalisation de la disposition des sous-projectiles 5 à l'intérieur du projectile 1 est donné sur la figure 4, qui est une vue en coupe transversale d'une moitié du projectile 1 de la figure 3a, au niveau de l'empennage des sous-projectiles de l'une des rangées 71, 72 ou 73.An embodiment of the arrangement of the sub-projectiles 5 inside the projectile 1 is given in FIG. 4, which is a cross-sectional view of one half of the projectile 1 of FIG. 3a, at the level of the tail of the sub-projectiles of one of the rows 71, 72 or 73.

Sur cette coupe, on a illustré l'enveloppe extérieure 3 et, vers le centre, un axe 20 supportant l'ogive 2 et une enveloppe intérieure 31.L'axe 20 de l'ogive est mobile dans l'enveloppe 31 pour permettre l'éjection de l'ogive, comme décrit plus loin. L'ensemble des sous-projectiles 5 est disposé entre les enveloppes 3 et 31.In this section, the outer casing 3 is illustrated and, towards the center, an axis 20 supporting the warhead 2 and an inner casing 31. The axis 20 of the warhead is movable in the casing 31 to allow the ejection of the warhead, as described below. All of the sub-projectiles 5 are disposed between the envelopes 3 and 31.

Dans ce mode de réalisation, la partie centrale (intérieur de l'enveloppe 31) du projectile ne comporte pas de sous-projectiles. Toutefois, les dimensions transversales de l'enveloppe 31 sont suffisamment faibles pour que cela ne se traduise pas, au niveau de la zone Z (figure 1) par une lacune gênante.In this embodiment, the central part (inside of the casing 31) of the projectile does not include sub-projectiles. However, the transverse dimensions of the envelope 31 are small enough so that this does not translate, at the level of the zone Z (FIG. 1), by an annoying gap.

On a également représenté sur la figure 4 le corps 54 de chacun des sous-projectiles 5 et leur empennage 56, les éléments 54 et 56 étant hachurés pour la clarté du dessin. Dans ce mode de réalisation, l'empennage de chaque sous-projectile 5 se compose de trois ailettes, disposées à 120°. Les corps 54 des sous-projectiles sont disposés selon un hexagone, dont un exemple est représenté en traits pointillés 74, le centre des corps 54 formant les sommets de l'hexagone et les corps 54 étant tangents les uns aux autres. Les ailettes sont disposées les unes dans les autres de telle sorte que la structure formée par l'ensemble des sous-projectiles soit auto-bloquante, c'est-à-dire qu'au centre de l'hexagone 74 on trouve six ailettes appartenant respectivement aux six sous-projectiles 5 de l'hexagone, bloquées les unes dans les autres.FIG. 4 also shows the body 54 of each of the sub-projectiles 5 and their tail unit 56, the elements 54 and 56 being hatched for the clarity of the drawing. In this embodiment, the tail of each sub-projectile 5 consists of three fins, arranged at 120 ° . The bodies 54 of the sub-projectiles are arranged in a hexagon, an example of which is shown in dotted lines 74, the center of the bodies 54 forming the vertices of the hexagon and the bodies 54 being tangent to each other. The fins are arranged one inside the other so that the structure formed by all of the sub-projectiles is self-locking, that is to say that in the center of hexagon 74 there are six fins belonging respectively to the six sub-projectiles 5 of the hexagon, blocked one inside the other.

Dans une variante préférée de réalisation, on dispose des éléments de calage intérieur 82 entre les sous-projectiles 5, au niveau des corps 54. Ces éléments 82 sont par exemple de forme sensiblement cylindrique et s'étendent sur toute la longueur des corps 54, ou seulement sur une partie de ceux-ci. Pour la clarté de la figure 2, la surface des éléments 82 est pointillée. Ces éléments de calage intérieurs 82 ont pour fonction d'améliorer la rigidité de l'ensemble des sous-projectiles 5, notamment dans le cas où le projectile est animé d'un mouvement de rotation autour de son axe longitudinal. Dans un mode de réalisation préféré, les éléments de calage 82 sont réalisés en un matériau souple, comme une mousse plastique, pré-contraint de façon à permettre de rattraper les éventuels jeux de la structure. Entre les sous-projectiles 5 et l'enveloppe intérieure 31, il peut être disposé comme représenté sur la figure 2 des éléments de calage tronqués, repérés 83, toujours dans le but d'améliorer la rigidité de structure.In a preferred embodiment, there are internal wedging elements 82 between the sub-projectiles 5, at the level of the bodies 54. These elements 82 are for example of substantially cylindrical shape and extend over the entire length of the bodies 54, or only on part of them. For the clarity of FIG. 2, the surface of the elements 82 is dotted. These internal wedging elements 82 have the function of improving the rigidity of all of the sub-projectiles 5, in particular in the case where the projectile is rotated around its longitudinal axis. In a preferred embodiment, the wedging elements 82 are made of a flexible material, such as plastic foam, pre-stressed so as to make it possible to make up for any play in the structure. Between the sub-projectiles 5 and the inner envelope 31, it may be arranged as shown in FIG. 2 truncated wedging elements, marked 83, again with the aim of improving the rigidity of the structure.

Entre la stucture formée par l'ensemble des sous-projectiles 5 et l'enveloppe extérieure 3, on dispose également des éléments de calage, repérés 81, ayant pour fonction d'éviter tout basculement vers l'extérieur des sous projectiles 5. Ces éléments 81 ont une forme adaptée à l'espace libre entre la structure formée par les sous-projectiles et l'enveloppe extérieure 3. Ils ne sont pas obligatoirement de section constante. Ils sont par exemple réalisés en un matériau plastique et sont de préférence en un matériau relativement rigide et susceptible de se morceler lors de l'éjection des sous-projectiles, selon un mécanisme décrit plus loin, de façon à ne pas perturber cette éjection.Between the structure formed by all of the sub-projectiles 5 and the outer casing 3, there are also wedging elements, marked 81, whose function is to prevent any tilting of the sub-projectiles to the outside 5. These elements 81 have a shape adapted to the free space between the structure formed by the sub-projectiles and the outer envelope 3. They are not necessarily of constant section. They are for example made of a plastic material and are preferably made of a relatively rigid material and capable of breaking up during the ejection of the sub-projectiles, according to a mechanism described below, so as not to disturb this ejection.

Les moyens de calage du chargement de sous-projectiles comportent encore des éléments de calage 84, analogues aux éléments 81, destinés à contenir le chargement et laisser l'espace 30 libre.The means for wedging the load of sub-projectiles also include wedging elements 84, similar to the elements 81, intended to contain the load and leave the space 30 free.

Enfin, les volumes laissés libres entre les parois 31 et 3, les sous-projectiles 5 et les éléments de calage 81, 82, 83 ou 84, sont remplis d'un matériau pulvérulent 9 dont la fonction est, d'une part, d'améliorer l'immobilisation des sous-projectiles 5 dans l'enveloppe 3 et, d'autre part, d'assurer une séparation entre chacune des rangées 71, 72 et 73 (figure 3a) pour une raison liée à l'éjection des sous-projectiles, comme exposé ci-après. Cette poudre 9 permet également de visualiser le point d'éjection des sous-projectiles, ce qui en facilite l'utilisation.Finally, the volumes left free between the walls 31 and 3, the sub-projectiles 5 and the wedging elements 81, 82, 83 or 84 are filled with a powder material 9 whose function is, on the one hand, to '' improve the immobilization of the sub-projectiles 5 in the envelope 3 and, on the other hand, to ensure a separation between each of the rows 71, 72 and 73 (Figure 3a) for a reason related to the ejection of the sub -projectiles, as set out below. This powder 9 also makes it possible to view the point of ejection of the sub-projectiles, which facilitates its use.

Le projectile principal 1 (figure 3a) comporte encore un disque 6 fermant l'espace entre les enveloppes 3 et 31 à l'arrière du chargement de sous-projectiles, ce disque 6 actionné par des moyens de propulsion 4 lors de l'éjection des sous-projectiles.The main projectile 1 (FIG. 3a) also includes a disc 6 closing the space between the envelopes 3 and 31 at the rear of the loading of sub-projectiles, this disc 6 actuated by propulsion means 4 during the ejection of the sub-projectiles.

Les figures 3b et 3c sont des schémas illustrant le mécanisme d'éjection des sous-projectiles 5 hors du projectile principal 1.FIGS. 3b and 3c are diagrams illustrating the mechanism for ejecting the sub-projectiles 5 from the main projectile 1.

Dans une première étape, sous l'action des moyens de propulsion 4 représentés schématiquement à l'arrière du projectile 1, l'axe 20 de l'ogive 2 coulisse à l'intérieur de l'enveloppe 31 jusqu'à ce que l'ogive se sépare du projectile. Celle-ci est dessinée de sorte qu'elle demeure alors stable et ne vienne pas perturber le mouvement des sous-projectiles en cours d'éjection ou celui du projectile principal.In a first step, under the action of the propulsion means 4 shown diagrammatically at the rear of the projectile 1, the axis 20 of the warhead 2 slides inside the casing 31 until the warhead separates from the projectile. This is designed so that it then remains stable and does not interfere with the movement of the sub-projectiles being ejected or that of the main projectile.

Dans une seconde étape, les moyens de propulsion 4 impriment un mouvement relatif vers l'avant au disque 6 par rapport à l'enveloppe 3, conduisant à l'éjection successive des rangées 71, 72 et 73 de sous-projectiles 5. Pendant l'éjection de l'ensemble des rangées 71-73, les éléments de calage 81-84 et le matériau pulvérulant 9 se séparent des sous-projectiles au fur et à mesure de leur apparition au bord de l'enveloppe 3.In a second step, the propulsion means 4 impart a relative forward movement to the disc 6 relative to the casing 3, leading to the successive ejection of the rows 71, 72 and 73 of sub-projectiles 5. During the ejection of all the rows 71-73, the wedging elements 81-84 and the pulverulent material 9 separate from the sub-projectiles as they appear at the edge of the envelope 3.

On a représenté sur la figure 3b le moment où l'ogive 2 est entièrement éjectée de l'enveloppe 3 et où la première des rangées, à savoir la rangée 71, est également entièrement éjectée.There is shown in Figure 3b the time when the warhead 2 is fully ejected from the casing 3 and when the first of the rows, namely row 71, is also fully ejected.

Ainsi qu'il est connu, chacun des sous-projectiles 5 est animé à sa sortie de l'enveloppe 3, outre d'une vitesse relative longitudinale, d'une vitesse radiale souvent appelée vitesse d'expansion, due à la force aérodynamique qui s'exerce sur eux à la sortie de l'enveloppe 3 et, le cas échéant, à la rotation sur lui-même du projectile principal. Par ailleurs, chacune des rangées est, lors de sa sortie, ralentie par cette force aérodynamique. Les deux phénomènes combinés permettent d'obtenir une interpénétration des différentes rangées, comme représenté sur la figure 3c où les trois rangées étant intégralement éjectées, les différents sous-projectiles 5 se retrouvent sensiblement sur la même ligne 74 pour former une gerbe unique, animée d'une vitesse longitudinale et d'une vitesse radiale d'expansion.As is known, each of the sub-projectiles 5 is animated at its exit from the envelope 3, in addition to a relative longitudinal speed, a radial speed often called expansion speed, due to the aerodynamic force which is exerted on them at the exit of the envelope 3 and, if necessary, at the rotation on itself of the main projectile. Furthermore, each of the rows is, when it leaves, slowed down by this aerodynamic force. The two phenomena combined make it possible to obtain an interpenetration of the different rows, as shown in FIG. 3c where the three rows being fully ejected, the different sub-projectiles 5 are found substantially on the same line 74 to form a single sheaf, animated by 'a longitudinal speed and a radial speed of expansion.

La vitesse radiale d'expansion est contrôlable, ce qui permet, avec le choix de la forme du chargement de sous-projectiles, d'adapter la forme de la gerbe à celle de la zone d'efficacité souhaitée. Cette vitesse d'expansion dépend de la vitesse de rotation du projectile principal 1, du dimensionnement des éléments de calage, des caractéristique géométriques des sous-projectiles et de leur position par rapport à l'axe longitudinal (XX) du projectile principal.The radial speed of expansion is controllable, which allows, with the choice of the shape of the loading of sub-projectiles, to adapt the shape of the spray to that of the desired efficiency zone. This speed of expansion depends on the speed of rotation of the main projectile 1, the dimensioning of the setting elements, the geometric characteristics of the sub-projectiles and their position relative to the longitudinal axis (XX) of the main projectile.

Les expériences et les calculs de la Déposante ont montré qu'il est en outre important que les têtes des sous-projectiles d'une rangée soient sans contact mécanique avec les arrières des sous-projectiles de la rangée précédente, pour éviter que le sous-projectile de derrière ne perturbe et fasse basculer le sous-projectile de devant. De plus, l'écartement entre les rangées doit être suffisant pour que l'inter-pénétration des rangées s'effectue correctement, sans contact (ou au moins avec un minimum de contact) entre sous-projectiles. Cette fonction de séparation est remplie, comme indiqué plus haut, par le matériau pulvérulent 9.The Depositor's experiments and calculations have shown that it is also important that the heads of the sub-projectiles of a row are without mechanical contact with the rear of the sub-projectiles of the previous row, to avoid that the sub-projectiles rear projectile does not disturb and tilts the front sub-projectile. In addition, the spacing between the rows must be sufficient for the inter-penetration of the rows to be carried out correctly, without contact (or at least with a minimum of contact) between sub-projectiles. This separation function is fulfilled, as indicated above, by the pulverulent material 9.

De la sorte, les sous-projectiles sont rigidement maintenus en place avant l'éjection de façon, au moment de l'éjection, à être aptes à suivre la trajectoire prévue. En outre, des moyens sont prévus pour que, lors de cette éjection , la trajectoire de chacun des sous-projectiles ne soit perturbée ni par les différents constituants du projectile principal, ni par les autres sous-projectiles..In this way, the sub-projectiles are rigidly held in place before ejection so as, at the time of ejection, to be able to follow the planned trajectory. In addition, means are provided so that, during this ejection, the trajectory of each of the sub-projectiles is neither disturbed by the various constituents of the main projectile, nor by the other sub-projectiles.

La description ci-dessus a été faite à titre d'exemple non limitatif. C'est ainsi que le projectile principal a été décrit comme ayant un corps cylindrique à sec-, tion circulaire, mais que cette section peut affecter d'autres formes, par exemple carrée, les sous-projectiles étant alors munis de quatre ailettes. Plus généralement, d'autres formes géométriques peuvent être utilisées pour le corps du projectile, le corps et l'empennage des sous-projectiles et leur organisation (en hexagone sur la figure 4), sous réserve que les corps des sous-projectiles soient tangents et leurs empennages organisés de façon autobloquante.The above description has been given by way of nonlimiting example. Thus the main projectile has been described as having a cylindrical body with a circular section, but this section can have other shapes, for example square, the sub-projectiles then being provided with four fins. More generally, other geometric shapes can be used for the body of the projectile, the body and the tail of the sub-projectiles and their organization (in hexagon in FIG. 4), provided that the bodies of the sub-projectiles are tangent and their tailplane organized in a self-locking manner.

Par ailleurs, on a décrit une application du type vecteur Air-Sol ou Sol-Sol. D'autres applications sont bien entendu possibles telles que celles où la zone cible est sur mer ou dans l'air (vecteur anti-hélicoptère par exemple).Furthermore, an application of the Air-Sol or Sol-Sol vector type has been described. Other applications are of course possible such as those where the target area is at sea or in the air (anti-helicopter vector for example).

Claims (3)

1. A projectile constituting the head of a missile with a predetermined ballistic trajectory (T), said projectile comprising sub-projectiles, characterized in that the projectile (1) includes means which ensure during the ejection of the sub-projectiles (5) that the latter remain on a predetermined trajectory, and that the shape of the cross-section (11) of the arrangement of these sub-projectiles (5) within the projectile is substantially homothetic with the shape of a predetermined efficiency zone (Z) after correction by the angle included between the trajectory (T) of the projectile and the efficiency zone.
2. A projectile according to claim 1, characterized in that the size of the cross-section (11) of the arrangement of sub-projectiles (5) depends on the radial expansion speed of the sub-projectiles.
3. A projectile according to one of the preceding claims, characterized in that each of the sub-projectiles (5) comprises a body (54) including a head (55) and fixed tail control surfaces (56), and that the means for maintaining the sub-projectiles on a predetermined trajectory are constituted by
- the arrangement of the sub-projectiles according to a common orientation, i.e. with the head towards the front end of the projectile (1) and according to at least one level (71 to 73), the sub-projectiles (5) being in each level (71 to 73) mutually tangent and the tail control surfaces (56) being nested one in the other in a self-locking manner,
- chocking means (81) disposed between the outer wall (43) of the projectile (1) and the structure constituted by the sub-projectiles (5),
- a powder substance (9) disposed in the interspaces left between the sub-projectiles (5) and the chocking means (81),
- means (4, 6) allowing the sub-projectiles (5) to be ejected, through the front side of the projectile (1).
EP87402969A 1986-12-31 1987-12-23 Carrier projectile with submissiles for creating a predetermined ground-striking pattern Expired - Lifetime EP0277445B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8618423 1986-12-31
FR8618423A FR2609165A1 (en) 1986-12-31 1986-12-31 PROJECTILE COMPRISING SUB-PROJECTILES WITH A PREFINED EFFICIENCY ZONE

Publications (2)

Publication Number Publication Date
EP0277445A1 EP0277445A1 (en) 1988-08-10
EP0277445B1 true EP0277445B1 (en) 1990-11-07

Family

ID=9342481

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87402969A Expired - Lifetime EP0277445B1 (en) 1986-12-31 1987-12-23 Carrier projectile with submissiles for creating a predetermined ground-striking pattern

Country Status (5)

Country Link
US (1) US4960055A (en)
EP (1) EP0277445B1 (en)
BR (1) BR8707096A (en)
DE (1) DE3766100D1 (en)
FR (1) FR2609165A1 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2747770B1 (en) * 1989-08-01 1998-12-18 Thomson Brandt Armements METHOD AND DEVICE FOR PREPARING A CONTROL FOR EJECTING SUBMUNITION CARRIED BY AIR-GROUND CARGO AMMUNITION
GB8918267D0 (en) * 1989-08-10 1990-04-25 British Aerospace Weapon systems
GB9014653D0 (en) * 1989-10-18 1997-11-05 Messerschmitt Boelkow Blohm Auswerfen und verteilen von submunition
US5649488A (en) * 1994-06-27 1997-07-22 The United States Of America As Represented By The Secretary Of The Navy Non-explosive target directed reentry projectile
NO311954B1 (en) * 1996-04-19 2002-02-18 Contraves Ag Procedure for determining a programmable projectile breakdown time
NO311953B1 (en) * 1996-04-19 2002-02-18 Contraves Ag Method and apparatus for determining the time of division of a programmable projectile
NO312143B1 (en) * 1996-04-19 2002-03-25 Contraves Ag Procedure for determining the desired split time, especially for a programmable projectile
US6279482B1 (en) * 1996-07-25 2001-08-28 Trw Inc. Countermeasure apparatus for deploying interceptor elements from a spin stabilized rocket
US6494140B1 (en) * 1999-04-22 2002-12-17 Lockheed Martin Corporation Modular rocket boosted penetrating warhead
US6640723B2 (en) * 2002-03-25 2003-11-04 The United States Of America As Represented By The Secretary Of The Navy Mission responsive ordnance
CA2541786C (en) 2003-10-14 2008-12-30 Raytheon Company Mine counter measure system
US7762196B1 (en) * 2007-04-12 2010-07-27 Lockheed Martin Corporation Munition containing sub-munitions that disperse in a circular delta grid impact pattern and method therefor
US8536500B2 (en) * 2008-08-07 2013-09-17 Cpi Ip, Llc System and method for rapid aiming and firing of defensive countermeasures
SE535304C2 (en) * 2010-03-18 2012-06-19 Bae Systems Bofors Ab Berry grenade packed with fin-stabilized penetrators

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE199366C (en) *
US1340871A (en) * 1917-06-21 1920-05-25 Vickers Ltd Explosive shell
FR621608A (en) * 1925-09-19 1927-05-14 Shrapnell with tapered projectiles fitted with a tail
US2809583A (en) * 1952-12-04 1957-10-15 Roman L Ortynsky Cluster bomb
US3088404A (en) * 1956-11-15 1963-05-07 Brown Fred Interlocking screw threads
US3093072A (en) * 1957-01-30 1963-06-11 George L Pigman Spin-induced dispersal bomb
US3599568A (en) * 1965-03-31 1971-08-17 Olin Mathieson Long-range shotshell
US3903804A (en) * 1965-09-27 1975-09-09 Us Navy Rocket-propelled cluster weapon
US3771455A (en) * 1972-06-06 1973-11-13 Us Army Flechette weapon system
US3881416A (en) * 1973-04-23 1975-05-06 Us Army Choked flechette weapon system
DE2934620C2 (en) * 1979-08-28 1981-10-22 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Procedure for covering an area with cluster munitions
US4777822A (en) * 1981-02-05 1988-10-18 Sumitomo Electric Industries, Ltd. Method of hot rolling copper
US4676167A (en) * 1986-01-31 1987-06-30 Goodyear Aerospace Corporation Spin dispensing method and apparatus

Also Published As

Publication number Publication date
FR2609165B1 (en) 1993-02-26
DE3766100D1 (en) 1990-12-13
BR8707096A (en) 1988-08-02
FR2609165A1 (en) 1988-07-01
EP0277445A1 (en) 1988-08-10
US4960055A (en) 1990-10-02

Similar Documents

Publication Publication Date Title
EP0270401B1 (en) Carrier projectile for dispersing subprojectiles in a controlled manner
EP0277445B1 (en) Carrier projectile with submissiles for creating a predetermined ground-striking pattern
EP0541411B1 (en) Device for ejecting submunitions from the shell of a cargomunition
EP0906556A1 (en) Non-lethal projectile
FR2526149A1 (en) ARM SYSTEM AND MUNITION OF OVERVOL
EP0438343B1 (en) Penetrator ammunition for targets with high mechanical resistance
FR2965908A1 (en) Device for neutralization of e.g. rocket, has deploying element deployed near target by deployment unit based on command delivered by synchronization unit and projected outside structure of carrier projectile
FR2657687A1 (en) ANTI-CHAR MUNITION AND METHOD OF USE
EP0130893B1 (en) Submunition dispensing projectile
EP0457657B1 (en) Penetrating projectile
EP0367815B1 (en) Separation device for the aerodynamic braking of a body
FR2950026A1 (en) METHOD AND SYSTEM FOR LAUNCHING TACTICAL OR STRATEGIC DEVICES HAVING AN AIRSPACE FROM THE SUBMARINE ENVIRONMENT
EP0229541A1 (en) Device for pitching projectiles during flight
FR2796454A1 (en) Weapon system mounted on stealth aircraft is concealed to minimize radar signature has concelaed tube fixed to the exterior and minmizes the reflection of electromagnetic waves
EP0918205B1 (en) Projectile having radial direction of action
EP0536048B1 (en) Mine for defending a zone
FR2644575A1 (en) OBJECTIVE MARKER FOR ATTRACTING PROJECTILES WITH SELF-DIAGRAM
EP0319379B1 (en) Launchable body with air brake means
FR2654822A1 (en) DISPENSER OF SUB-PROJECTILES.
EP0799148B1 (en) Braking shield for a spacecraft and satellite provided therewith
EP2569591A1 (en) Guided munition protected by an aerodynamic cap
FR2622966A1 (en) GYROSCOPIC STABILIZATION DEVICE FOR A PROJECTILE MANEUVER ORGAN
EP1521053A1 (en) Anti-bunker ammunition
EP0482970A1 (en) Device for imparting a deviated trajectory to an airborne missile
FR2523717A1 (en) Anti-tank weapon system - including carrier projectile dropping vertically into battlefield before releasing separate shells during rapid rotation

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): BE CH DE GB IT LI SE

17P Request for examination filed

Effective date: 19881230

17Q First examination report despatched

Effective date: 19900326

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): BE CH DE GB IT LI SE

ITF It: translation for a ep patent filed

Owner name: JACOBACCI & PERANI S.P.A.

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 19901119

Year of fee payment: 4

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19901123

Year of fee payment: 4

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19901126

Year of fee payment: 4

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: BE

Payment date: 19901128

Year of fee payment: 4

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
REF Corresponds to:

Ref document number: 3766100

Country of ref document: DE

Date of ref document: 19901213

ITTA It: last paid annual fee
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19911223

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19911224

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19911231

Ref country code: CH

Effective date: 19911231

Ref country code: BE

Effective date: 19911231

BERE Be: lapsed

Owner name: THOMSON-BRANDT ARMEMENTS

Effective date: 19911231

GBPC Gb: european patent ceased through non-payment of renewal fee
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19920901

EUG Se: european patent has lapsed

Ref document number: 87402969.7

Effective date: 19920704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20051223