EP0277445B1 - Trägergeschoss zum Belegen einer vorgewählten Fläche mit Streumunition - Google Patents

Trägergeschoss zum Belegen einer vorgewählten Fläche mit Streumunition Download PDF

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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
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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
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English (en)
French (fr)
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EP0277445A1 (de
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
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Thomson Brandt Armements SA
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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
    • 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).

Claims (3)

1. Geschoß an der Spitze einer Trägerrakete mit einer definierten ballistischen Flugbahn (T), wobei das Geschoß Sekundärgeschosse aufweist, dadurch gekennzeichnet, daß das Geschoß (1) Mittel aufweist, die während des Ausstoßens der Sekundärgeschosse (5) dafür sorgen, daß letztere auf einer vorgegebenen Flugbahn bleiben, und daß die Form des Querschnitts (11) der Ladeanordnung der Sekundärgeschosse (5) im Geschoß im wesentlichen ein homothetisches Abbild der Form einer vorbestimmten Wirkungszone (Z) ist, die um den Winkel korrigiert ist, den die Flugbahn (T) des Geschosses mit der Wirkungszone einschließt.
2. Geschoß nach Anspruch 1, dadurch gekennzeichnet, daß die Abmessungen des für die Ladung von Sekundärgeschossen (5) bestimmten Querschnitts (11) von der radialen Streugeschwindigkeit der Sekundärgeschosse abhängt.
3. Geschoß nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß jedes der Sekundärgeschosse (5) einen Körper (54) mit einem Kopf (55) und einem festen Leitwerk (56) aufweist und daß die Mittel, um die Sekundärgeschosse auf einer vorgegebenen Flugbahn zu halten, bestehen aus
- der Anordnung der Sekundärgeschosse gemäß einer gleichen Orientierung, nämlich mit dem Kopf zur Vorderseite des Geschosses (1) und in mindestens einer Reihe (71 bis 73), wobei in jeder Reihe (71 bis 73) die Sekundärgeschosse (5) einander berühren und die Leitwerke (56) ineinander so angeordnet sind, daß sie sich selbst blockieren,
- Distanzmitteln (81), die zwischen der Außenwand (3) des Geschosses (1) und der von den Sekundärgeschossen (5) gebildeten Struktur angeordnet sind,
- einer pulverförmigen Substanz (9), die in den zwischen den Sekundärgeschossen (5) und den Distanzmitteln (81) verbleibenden Zwischenräumen angeordnet ist,
- Mitteln (4, 6), die einen Ausstoß der Sekundärgeschosse (5) durch die Vorderseite des Geschosses (1) bewirken.
EP87402969A 1986-12-31 1987-12-23 Trägergeschoss zum Belegen einer vorgewählten Fläche mit Streumunition Expired - Lifetime EP0277445B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8618423A FR2609165A1 (fr) 1986-12-31 1986-12-31 Projectile comportant des sous-projectiles a zone d'efficacite predefinie
FR8618423 1986-12-31

Publications (2)

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

Family

ID=9342481

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87402969A Expired - Lifetime EP0277445B1 (de) 1986-12-31 1987-12-23 Trägergeschoss zum Belegen einer vorgewählten Fläche mit Streumunition

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US (1) US4960055A (de)
EP (1) EP0277445B1 (de)
BR (1) BR8707096A (de)
DE (1) DE3766100D1 (de)
FR (1) FR2609165A1 (de)

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FR2747770B1 (fr) * 1989-08-01 1998-12-18 Thomson Brandt Armements Procede et dispositif d'elaboration de commande d'ejection des sous-munitions portees par une munition air-sol de type cargo
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
NO311953B1 (no) * 1996-04-19 2002-02-18 Contraves Ag Fremgangsmåte og innretning for å bestemme et programmerbart prosjektils oppdelingstidspunkt
NO312143B1 (no) * 1996-04-19 2002-03-25 Contraves Ag Fremgangsmåte for å bestemme önsket oppdelingstidspunkt, s¶rlig for et programmerbart prosjektil
NO311954B1 (no) * 1996-04-19 2002-02-18 Contraves Ag Fremgangsmåte for å bestemme et programmerbart prosjektils oppdelingstidspunkt
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 (sv) * 2010-03-18 2012-06-19 Bae Systems Bofors Ab Bärgranat packad med fenstabiliserade penetratorer

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Also Published As

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

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