EP1953494B1 - Device for controlling ammunition with deployable control surfaces - Google Patents

Device for controlling ammunition with deployable control surfaces Download PDF

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Publication number
EP1953494B1
EP1953494B1 EP08290062A EP08290062A EP1953494B1 EP 1953494 B1 EP1953494 B1 EP 1953494B1 EP 08290062 A EP08290062 A EP 08290062A EP 08290062 A EP08290062 A EP 08290062A EP 1953494 B1 EP1953494 B1 EP 1953494B1
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EP
European Patent Office
Prior art keywords
pinion
ammunition
gear
support
attitude control
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EP08290062A
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German (de)
French (fr)
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EP1953494A1 (en
Inventor
Cécile Grognet-Quenecan
René Dodu
Geoffroy Deschatre
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Nexter Munitions SA
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Nexter Munitions SA
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Publication of EP1953494A1 publication Critical patent/EP1953494A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

  • the technical field of the invention is that of ammunition control devices comprising control surfaces, such a device is described for example in the US Patent 5,630,564 A1 .
  • control surfaces that deploy on trajectory after the firing of the ammunition, control surfaces whose pivot control allows to control the trajectory of the ammunition.
  • Licences FR-2864613 and FR-2846080 thus describe known devices associating a mechanism of deployment of control surfaces and a drive mechanism thereof.
  • control surfaces arranged behind the ammunition body or control surfaces disposed at the front of the munition body ("duck" control surfaces).
  • the purpose of the invention is to propose a control device having a minimal bulk, both at the level of governes itself at the level of the drive mechanism of these control surfaces.
  • the subject of the invention is a device for driving an ammunition, or a submunition, comprising integral control surfaces of a body of the munition and each pivoted by a geared motor, a device characterized in that the control surfaces are formed of elastic sheets foldable by winding around a rear part of the body of the munition and likely to take place to adopt a substantially radial position relative to the body of the ammunition, each surface comprising a support carrying the sheets forming the steering plane, support which is articulated relative to the body of the ammunition at a pivot disposed in front of the steering plane, the support also carrying a rear rack meshing with a pinion driven by the gear reduction motorcycle.
  • the support may comprise a rear tongue which will be held radially by an abutment surface secured to the body of the munition, the tongue sliding on the abutment surface during the pivoting of the rudder.
  • the rack will be advantageously conical.
  • the pinion driving the rack may include a conical portion cooperating with the rack and a cylindrical portion cooperating with a gear driven by the gear motor
  • the cylindrical portion can cooperate via a gear inverter with the gear driven by the gear motor.
  • the figure 1 shows a cargo shell 1 having a body 2 closed by a base 3.
  • the body 2 carries at its front part a rocket 4 and at its rear part a belt 5 sealing the propellant when fired in a weapon.
  • the shell 1 contains a submunition 6 which is equipped with a control device according to the invention (not visible in this figure).
  • the submunition is released on the trajectory by the shell 1 by means of a gas generating composition which is initiated by the rocket 4.
  • the pressure of the gases that are generated inside the shell 1 in the vicinity of the rocket 4 push the submunition 6 backwards. This one then pushes the base 3 whose connection is sheared.
  • the pellet is ejected and the submunition also.
  • FIG. 1 shows a cylinder 7 which ensures, on the one hand, the maintenance of the control surfaces of the sub ammunition 6 and secondly the braking in rotation of the latter.
  • the figure 3 shows the separate submunition of the cylinder 7. It can be seen that the cylinder 7 carries radial wings 8 which, when deployed at the exit of the body of the shell 1, provide rotational braking of the submunition.
  • the cylinder 7 releases in turn the sub-munition 6 itself.
  • the separation between the latter and the cylinder 7 is ensured by means of a gas generating composition (not shown) which is initiated by a safety device and firing at the end of a time period counted from the first expulsion (expulsion cylinder + under ammunition).
  • a plate 10 which is interposed between the submunition 6 and the bottom of the cylinder 7. It is intended to provide a rotational connection of these two elements during firing and braking in rotation. It constitutes the thrust plate of the submunition during this second expulsion.
  • control surfaces 9 integral with the body of the sub-munition 6 are formed of elastic sheets foldable by winding around a rear portion 12 of the body of the submunition 6.
  • the figure 2a shows in a simplified way the control surfaces 9 in their folded position.
  • the figure 2b shows these same control surfaces in their deployed position.
  • Each rudder is formed by the assembly of two thin steel sheets which are welded along their edges and which form once assembled a plane of rudder. This steering plane is delimited by the leading edge BA and the trailing edge BF (see figure 4 ).
  • the space between the sheets is hollow.
  • the sheets are also both fixed to a support 11 which is integral with the body of the sub-munition 6.
  • control surfaces 9 In this deployed position the control surfaces 9 have a substantially radial orientation relative to the body of the ammunition 6.
  • control surfaces are held radially in their folded position by the cylinder 7.
  • the ejection of the cylinder 7 allows the control surfaces to be deployed ( figure 3 ).
  • each rudder 9 is fixed to a support 11 by two welded flanges 13. These flanges are introduced into holes pierced on the sheets and they allow the deformation and the bringing together of the two sheets during the folding and unfolding movements.
  • the support 11 is articulated relative to the body of the submunition 6 at a pivot 14 which is disposed in front of the steering plane 9.
  • the support 11 also carries a rear rack 15 which meshes with a pinion 16 , driven by a steering gear motorcycle.
  • the gear motor is not visible on the figure 5 but it is coaxial with a gear 18 which drives the pinion 16, either directly or by means of a reversing pinion 17.
  • the device according to the invention comprises four geared motors, each driving a rudder 9. These geared motors have their axes parallel to the axis of the submunition.
  • the device has two stages of knuckles 26a and 26b superimposed axially.
  • Two geared motors 25a each have a short shaft carrying a gear 18 which directly drives a pinion 16. These gears and gears form the first stage 26a.
  • Two other geared motors 25b are provided with a long shaft which carries a gear 18 which drives another pinion 16 via a reversing pinion 17. These gears and pinions form the second stage 26b.
  • the first stage 26a thus consists of two identical sets each comprising a gear 18 mounted on a short motor shaft and which drives a pinion 16.
  • the pinions and gears of this first stage are shown in broken lines on the figure 6b .
  • the second stage 26b consists of two identical assemblies each comprising a gear 18 mounted on a long motor shaft and which drives a pinion 16 via a reversing pinion 17.
  • the components of this second stage are represented in solid lines on the figure 6b .
  • This two-stage distribution of the gears makes it easy to house the geared motors while ensuring control surfaces are driven using a compact and robust mechanism.
  • the submunition body 6 has at its rear portion 12 a countersunk housing 19 (see figure 5 ) which is delimited by two intersecting planes 20 which converge in the direction of the pivot 14.
  • This housing 19 is extended by two lateral recesses 21 which allow the passage of the rack 15 during the pivoting of the rudder (see also figure 4 ).
  • the pivoting of the support 11 takes place in a plane (which is materialized by the bottom of the milled housing 19. Given the flatness of this movement while the pinions 16 are fixed and axes parallel to the axis of the sub 6, the rack 15 has a conical profile and cooperates with a conical portion 16a of the pinion 16.
  • the pinion 16 further comprises a cylindrical portion 16b which cooperates with the gear 18 (or with the inverter pinion 17).
  • each support comprises a rear tongue 22.
  • This tongue forms a friction pad which is held radially by an abutment surface 23 secured to the body of the submunition 6 ( figure 4 ).
  • This abutment surface 23 is an insert on a bottom 24 secured to the submunition and which closes the housing of the different gears.
  • each support 11 slides on the abutment surface 23 which also ensures its mechanical retention.
  • the device according to the invention has a certain number of advantages.
  • each rudder 9 is relatively wide, the mechanical drive means can be housed very behind the sub-munition thus releasing a significant volume for the payload.
  • each rudder 9 is made possible by the articulation of each rudder 9 at a pivot 14 located in front of the leading edge (BA) of the rudder while the rotation drive is provided by a motor that meshes with a rack next to the trailing edge (BF) of the rudder.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)
  • Accommodation For Nursing Or Treatment Tables (AREA)
  • Manipulator (AREA)
  • Catching Or Destruction (AREA)
  • Sowing (AREA)
  • Toys (AREA)

Abstract

The device has a control surface (9) placed in a body of an ammunition. The surface is formed by elastic sheets that are folded by rolling around a back part (12) of the ammunition body and are unrolled to adopt a radial position with respect to the body. The surface includes a support (11) carrying the sheets formed in a plane of the surface. The support is articulated with respect to the body at level of a pivot (14) that is placed in front of the surface plane. The support carries a back toothed conical rack (15) intermeshed on a pinion (16) driven by a controlling gear motor.

Description

Le domaine technique de l'invention est celui des dispositifs de pilotage de munition comprenant des gouvernes, un tel dispositif est décrit par exemple dans le brevet US 5 630 564 A1 .The technical field of the invention is that of ammunition control devices comprising control surfaces, such a device is described for example in the US Patent 5,630,564 A1 .

Il est classique de mettre en oeuvre des gouvernes qui se déploient sur trajectoire après le tir de la munition, gouvernes dont la commande de pivotement permet de maîtriser la trajectoire de la munition.It is conventional to implement control surfaces that deploy on trajectory after the firing of the ammunition, control surfaces whose pivot control allows to control the trajectory of the ammunition.

Les brevets FR-2864613 et FR-2846080 décrivent ainsi des dispositifs connus associant un mécanisme de déploiement de gouvernes et un mécanisme d'entraînement de ces dernières.Licences FR-2864613 and FR-2846080 thus describe known devices associating a mechanism of deployment of control surfaces and a drive mechanism thereof.

Suivant le cas on utilise des gouvernes disposées en arrière du corps de munition ou bien des gouvernes disposées à l'avant du corps de munition (gouvernes "canard").Depending on the case we use control surfaces arranged behind the ammunition body or control surfaces disposed at the front of the munition body ("duck" control surfaces).

Les dispositifs connus présentent l'inconvénient d'être encombrants car ils pénètrent à l'intérieur du corps de la munition.Known devices have the disadvantage of being bulky because they penetrate inside the body of the munition.

Ils réduisent ainsi le volume de la charge utile emportée par la munition. Un tel défaut est particulièrement pénalisant lorsque la munition est une sous munition qui est dispersée sur trajectoire par un obus cargo d'artillerie. En effet dans ce cas le volume de la sous munition est réduit et la place utilisable par le dispositif de pilotage est donc également réduite.They thus reduce the volume of the payload carried by the munition. Such a defect is particularly disadvantageous when the ammunition is a submunition which is dispersed on the trajectory by an artillery cargo shell. Indeed in this case the volume of the submunition is reduced and the place usable by the control device is also reduced.

Les dispositifs connus sont également complexes. Ils doivent combiner un mouvement de déploiement et un mouvement de commande de pilotage, mouvements dont les axes sont le plus souvent perpendiculaires l'un à l'autre. De tels mécanismes sont décrits en détails par les brevets FR2864613 et FR2846080 .Known devices are also complex. They must combine a deployment movement and a steering control movement, movements whose axes are usually perpendicular to each other. Such mechanisms are described in detail by patents FR2864613 and FR2846080 .

On a proposé dans le brevet FR2623898 un dispositif plus particulièrement adapté à une sous munition dispersable et dans lequel les gouvernes sont disposées tangentiellement au corps de la sous munition. Cependant un tel dispositif est encore trop encombrant notamment du point de vue de sa motorisation qui comporte plusieurs moto réducteurs, disposés chacun dans le prolongement de l'axe d'une gouverne.It has been proposed in the patent FR2623898 a device more particularly adapted to a dispersible submunition and in which the control surfaces are arranged tangentially to the body of the submunition. However, such a device is still too bulky, particularly from the point of view of its motorization which comprises several geared motors, each arranged in the extension of the axis of a rudder.

L'invention a pour but de proposer un dispositif de pilotage ayant un encombrement minimal, tant au niveau des gouvernes elle mêmes qu'au niveau du mécanisme d'entraînement de ces gouvernes.The purpose of the invention is to propose a control device having a minimal bulk, both at the level of governes itself at the level of the drive mechanism of these control surfaces.

Ainsi l'invention a pour objet un dispositif de pilotage d'une munition, ou d'une sous-munition, comprenant des gouvernes solidaires d'un corps de la munition et commandées chacune en pivotement par un moto réducteur, dispositif caractérisé en ce que les gouvernes sont formées de tôles élastiques repliables par enroulement autour d'une partie arrière du corps de la munition et susceptibles de se dérouler pour adopter une position sensiblement radiale par rapport au corps de la munition, chaque gouverne comprenant un support portant les tôles formant le plan de gouverne, support qui est articulé par rapport au corps de la munition au niveau d'un pivot disposé en avant du plan de gouverne, le support portant également une crémaillère arrière engrenant sur un pignon entraîné par le moto réducteur de pilotage.Thus, the subject of the invention is a device for driving an ammunition, or a submunition, comprising integral control surfaces of a body of the munition and each pivoted by a geared motor, a device characterized in that the control surfaces are formed of elastic sheets foldable by winding around a rear part of the body of the munition and likely to take place to adopt a substantially radial position relative to the body of the ammunition, each surface comprising a support carrying the sheets forming the steering plane, support which is articulated relative to the body of the ammunition at a pivot disposed in front of the steering plane, the support also carrying a rear rack meshing with a pinion driven by the gear reduction motorcycle.

Le support pourra comporter une languette arrière qui sera maintenue radialement par une surface de butée solidaire du corps de la munition, la languette glissant sur la surface de butée lors du pivotement de la gouverne.The support may comprise a rear tongue which will be held radially by an abutment surface secured to the body of the munition, the tongue sliding on the abutment surface during the pivoting of the rudder.

La crémaillère sera avantageusement conique.The rack will be advantageously conical.

Le pignon entraînant la crémaillère pourra ainsi comporter une partie conique coopérant avec la crémaillère et une partie cylindrique coopérant avec un engrenage entraîné par le moto réducteurThe pinion driving the rack and may include a conical portion cooperating with the rack and a cylindrical portion cooperating with a gear driven by the gear motor

En particulier, la partie cylindrique peut coopérer par l'intermédiaire d'un pignon inverseur avec l'engrenage entraîné par le moto réducteur.In particular, the cylindrical portion can cooperate via a gear inverter with the gear driven by the gear motor.

Le dispositif de pilotage pourra plus précisément comprendre quatre moto réducteurs :

  • deux moto réducteurs dotés d'un arbre moteur court portant un engrenage attaquant le pignon et
  • deux moto réducteurs dotés d'un arbre moteur long portant un engrenage qui attaque le pignon par l'intermédiaire d'un pignon inverseur.
The steering device may more precisely include four geared motors:
  • two geared motors with a short motor shaft carrying gear gearing the pinion and
  • two geared motors with a long drive shaft carrying a gear that drives the pinion via a reversing gear.

L'invention sera mieux comprise à la lecture de la description qui va suivre de différents modes de réalisation, description faite en référence aux dessins annexés et dans lesquels :

  • la figure 1 est une vue schématique en coupe partielle d'un obus cargo renfermant une sous munition équipée d'un dispositif selon l'invention,
  • les figures 2a et 2b sont deux vues montrant deux étapes du déploiement des gouvernes,
  • la figure 3 est une vue en perspective montrant la séparation de la sous munition et de son cylindre de freinage,
  • la figure 4 est une vue de l'arrière de la sous munition montrant un mode de réalisation du dispositif selon l'invention,
  • la figure 5 est une vue, partiellement écorchée, montrant différents composants du dispositif de déploiement selon l'invention,
  • les figures 6a et 6b sont des vues schématiques montrant l'implantation des moto réducteurs et des différents étages de pignoneries, la figure 6b est une vue de l'arrière de la munition suivant la direction d'observation D repérée figure 6a.
The invention will be better understood on reading the following description of various embodiments, description made with reference to the accompanying drawings and in which:
  • the figure 1 is a schematic partial sectional view of a cargo shell containing a sub-munition equipped with a device according to the invention,
  • the Figures 2a and 2b are two views showing two stages of the deployment of the control surfaces,
  • the figure 3 is a perspective view showing the separation of the submunition and its brake cylinder,
  • the figure 4 is a view from the rear of the submunition showing an embodiment of the device according to the invention,
  • the figure 5 is a view, partially broken away, showing different components of the deployment device according to the invention,
  • the Figures 6a and 6b are schematic views showing the implementation of geared motors and different stages of gear, the figure 6b is a view from the rear of the ammunition following the observation direction D spotted figure 6a .

La figure 1 montre un obus cargo 1 comportant un corps 2 fermé par un culot 3. Le corps 2 porte à sa partie avant une fusée 4 et à sa partie arrière une ceinture 5 assurant l'étanchéité aux gaz propulsifs lors du tir dans un arme.The figure 1 shows a cargo shell 1 having a body 2 closed by a base 3. The body 2 carries at its front part a rocket 4 and at its rear part a belt 5 sealing the propellant when fired in a weapon.

L'obus 1 renferme une sous-munition 6 qui est équipée d'un dispositif de pilotage selon l'invention (non visible sur cette figure).The shell 1 contains a submunition 6 which is equipped with a control device according to the invention (not visible in this figure).

D'une façon classique la sous munition est libérée sur trajectoire par l'obus 1 au moyen d'une composition génératrice de gaz qui est initiée par la fusée 4. La pression des gaz qui sont engendrés à l'intérieur de l'obus 1 au voisinage de la fusée 4 pousse la sous munition 6 vers l'arrière. Celle ci pousse alors le culot 3 dont la liaison est cisaillée. Le culot est éjecté et la sous munition également.In a conventional manner the submunition is released on the trajectory by the shell 1 by means of a gas generating composition which is initiated by the rocket 4. The pressure of the gases that are generated inside the shell 1 in the vicinity of the rocket 4 push the submunition 6 backwards. This one then pushes the base 3 whose connection is sheared. The pellet is ejected and the submunition also.

On a représenté en grisé sur la figure 1 un cylindre 7 qui assure, d'une part le maintien des gouvernes de la sous munition 6 et d'autre part le freinage en rotation de cette dernière. La figure 3 montre la sous munition séparée du cylindre 7. On voit que le cylindre 7 porte des ailes radiales 8 qui, en se déployant à la sortie du corps de l'obus 1, assurent le freinage en rotation de la sous munition.We have shown in gray on the figure 1 a cylinder 7 which ensures, on the one hand, the maintenance of the control surfaces of the sub ammunition 6 and secondly the braking in rotation of the latter. The figure 3 shows the separate submunition of the cylinder 7. It can be seen that the cylinder 7 carries radial wings 8 which, when deployed at the exit of the body of the shell 1, provide rotational braking of the submunition.

Après ce freinage, le cylindre 7 libère à son tour la sous munition 6 elle-même. La séparation entre cette dernière et le cylindre 7 est assurée au moyen d'une composition génératrice de gaz (non représentée) qui est initiée par un dispositif de sécurité et de mise à feu à l'issue d'un délai compté à partir de la première expulsion (expulsion cylindre + sous munition).After this braking, the cylinder 7 releases in turn the sub-munition 6 itself. The separation between the latter and the cylinder 7 is ensured by means of a gas generating composition (not shown) which is initiated by a safety device and firing at the end of a time period counted from the first expulsion (expulsion cylinder + under ammunition).

On voit sur la figure 3 une plaque 10 qui se trouve interposée entre la sous munition 6 et le fond du cylindre 7. Elle est destinée à assurer une solidarisation en rotation de ces deux éléments lors du tir et du freinage en rotation. Elle constitue la plaque de poussée de la sous munition lors de cette seconde expulsion.We see on the figure 3 a plate 10 which is interposed between the submunition 6 and the bottom of the cylinder 7. It is intended to provide a rotational connection of these two elements during firing and braking in rotation. It constitutes the thrust plate of the submunition during this second expulsion.

Conformément à une première caractéristique de l'invention, les gouvernes 9 solidaires du corps de la sous munition 6 sont formées de tôles élastiques, repliables par enroulement autour d'une partie arrière 12 du corps de la sous-munition 6.According to a first characteristic of the invention, the control surfaces 9 integral with the body of the sub-munition 6 are formed of elastic sheets foldable by winding around a rear portion 12 of the body of the submunition 6.

La figure 2a montre de façon simplifiée les gouvernes 9 dans leur position repliée. La figure 2b montre ces mêmes gouvernes dans leur position déployée. Chaque gouverne est formée par l'assemblage de deux tôles d'acier minces qui sont soudées le long de leurs bords et qui forment une fois assemblées un plan de gouverne. Ce plan de gouverne est délimité par le bord d'attaque BA et le bord de fuite BF (voir figure 4). L'espace entre les tôles est creux. Les tôles sont par ailleurs toutes deux fixées à un support 11 qui est solidaire du corps de la sous munition 6.The figure 2a shows in a simplified way the control surfaces 9 in their folded position. The figure 2b shows these same control surfaces in their deployed position. Each rudder is formed by the assembly of two thin steel sheets which are welded along their edges and which form once assembled a plane of rudder. This steering plane is delimited by the leading edge BA and the trailing edge BF (see figure 4 ). The space between the sheets is hollow. The sheets are also both fixed to a support 11 which is integral with the body of the sub-munition 6.

Il est possible de déformer une telle gouverne pour la replier et l'enrouler autour du corps de la sous munition 6. Une telle forme de gouverne est bien connue et décrite notamment par les brevets DE4025515 , EP333681 et EP905473 .It is possible to deform such a rudder to fold it and wrap around the body of the submunition 6. Such a form of rudder is well known and described in particular by patents DE4025515 , EP333681 and EP905473 .

Elle présente l'avantage de ne pas imposer un moyen de déploiement complexe puisque c'est l'élasticité même du matériau des gouvernes qui assure leur déploiement, c'est à dire leur passage de la position repliée (figure 2a) à la position déployée de la figure 2b (ouverture suivant les flèches D).It has the advantage of not imposing a complex deployment means since it is the elasticity of the material of the control surfaces that ensures their deployment, that is to say their passage from the folded position ( figure 2a ) at the deployed position of the figure 2b (opening following the arrows D).

Dans cette position déployée les gouvernes 9 ont une orientation sensiblement radiale par rapport au corps de la munition 6.In this deployed position the control surfaces 9 have a substantially radial orientation relative to the body of the ammunition 6.

Les gouvernes sont maintenues radialement dans leur position repliée par le cylindre 7. L'éjection du cylindre 7 permet le déploiement des gouvernes (figure 3).The control surfaces are held radially in their folded position by the cylinder 7. The ejection of the cylinder 7 allows the control surfaces to be deployed ( figure 3 ).

Les figures 4 et 5 montrent d'une façon plus précise la structure du dispositif de pilotage selon l'invention.The figures 4 and 5 show in a more precise manner the structure of the control device according to the invention.

Pour la clarté de la représentation on a retiré sur la figure 5 une partie des pièces et on a découpé par ailleurs le corps de la sous-munition 6 pour montrer la structure interne.For the sake of clarity, we have removed the figure 5 part of the pieces and the body of the submunition 6 has been cut out to show the internal structure.

On voit que chaque gouverne 9 est fixée à un support 11 par deux brides soudées 13. Ces brides sont introduites dans des lumières percées sur les tôles et elles autorisent la déformation et le rapprochement des deux tôles lors des mouvements de repli et de déploiement.It can be seen that each rudder 9 is fixed to a support 11 by two welded flanges 13. These flanges are introduced into holes pierced on the sheets and they allow the deformation and the bringing together of the two sheets during the folding and unfolding movements.

Le support 11 est articulé par rapport au corps de la sous-munition 6 au niveau d'un pivot 14 qui est disposé en avant du plan de gouverne 9. Par ailleurs le support 11 porte également une crémaillère arrière 15 qui engrène sur un pignon 16, entraîné par un moto réducteur de pilotage.The support 11 is articulated relative to the body of the submunition 6 at a pivot 14 which is disposed in front of the steering plane 9. In addition, the support 11 also carries a rear rack 15 which meshes with a pinion 16 , driven by a steering gear motorcycle.

Le moto réducteur n'est pas visible sur la figure 5 mais il se trouve coaxial à un engrenage 18 qui entraîne le pignon 16, soit directement, soit par l'intermédiaire d'un pignon inverseur 17.The gear motor is not visible on the figure 5 but it is coaxial with a gear 18 which drives the pinion 16, either directly or by means of a reversing pinion 17.

Le dispositif selon l'invention comporte quatre moto réducteurs, chacun entraînant une gouverne 9. Ces moto réducteurs ont leurs axes parallèles à l'axe de la sous-munition.The device according to the invention comprises four geared motors, each driving a rudder 9. These geared motors have their axes parallel to the axis of the submunition.

Comme cela apparaît sur les figures 5, 6a et 6b le dispositif comporte deux étages de pignonneries 26a et 26b superposés axialement. Deux moto réducteurs 25a sont dotés chacun d'un arbre court portant un engrenage 18 qui attaque directement un pignon 16. Ces engrenages et pignons forment le premier étage 26a.As it appears on the figures 5 , 6a and 6b the device has two stages of knuckles 26a and 26b superimposed axially. Two geared motors 25a each have a short shaft carrying a gear 18 which directly drives a pinion 16. These gears and gears form the first stage 26a.

Deux autres moto réducteurs 25b sont dotés d'un arbre long qui porte un engrenage 18 qui entraîne un autre pignon 16 par l'intermédiaire d'un pignon inverseur 17. Ces engrenages et pignons forment le deuxième étage 26b.Two other geared motors 25b are provided with a long shaft which carries a gear 18 which drives another pinion 16 via a reversing pinion 17. These gears and pinions form the second stage 26b.

Le premier étage 26a est donc constitué de deux ensembles identiques comprenant chacun un engrenage 18 monté sur un arbre moteur court et qui attaque un pignon 16. Les pignons et engrenages de ce premier étage sont représentés en traits interrompus sur la figure 6b.The first stage 26a thus consists of two identical sets each comprising a gear 18 mounted on a short motor shaft and which drives a pinion 16. The pinions and gears of this first stage are shown in broken lines on the figure 6b .

Le second étage 26b est constitué de deux ensembles identiques comprenant chacun un engrenage 18 monté sur un arbre moteur long et qui attaque un pignon 16 par l'intermédiaire d'un pignon inverseur 17. Les composants de ce deuxième étage sont représentés en traits pleins sur la figure 6b.The second stage 26b consists of two identical assemblies each comprising a gear 18 mounted on a long motor shaft and which drives a pinion 16 via a reversing pinion 17. The components of this second stage are represented in solid lines on the figure 6b .

Cette répartition des pignons en deux étages permet de loger facilement les moto réducteurs tout en assurant l'entraînement des gouvernes à l'aide d'un mécanisme compact et robuste.This two-stage distribution of the gears makes it easy to house the geared motors while ensuring control surfaces are driven using a compact and robust mechanism.

Pour permettre le pivotement du support 11 par rapport au pivot 14, le corps de sous-munition 6 comporte au niveau de sa partie arrière 12 un logement fraisé 19 (voir figure 5) qui est délimité par deux plans sécants 20 qui convergent en direction du pivot 14. Ce logement 19 est prolongé par deux dégagements latéraux 21 qui permettent le passage de la crémaillère 15 lors du pivotement de la gouverne (voir aussi figure 4).To allow pivoting of the support 11 relative to the pivot 14, the submunition body 6 has at its rear portion 12 a countersunk housing 19 (see figure 5 ) which is delimited by two intersecting planes 20 which converge in the direction of the pivot 14. This housing 19 is extended by two lateral recesses 21 which allow the passage of the rack 15 during the pivoting of the rudder (see also figure 4 ).

Le pivotement du support 11 s'effectue dans un plan (qui est matérialisé par le fond du logement fraisé 19. Compte tenu de la planéité de ce mouvement alors que les pignons 16 sont fixes et d'axes parallèles à l'axe de la sous-munition 6, la crémaillère 15 a un profil conique et coopère avec une partie conique 16a du pignon 16.The pivoting of the support 11 takes place in a plane (which is materialized by the bottom of the milled housing 19. Given the flatness of this movement while the pinions 16 are fixed and axes parallel to the axis of the sub 6, the rack 15 has a conical profile and cooperates with a conical portion 16a of the pinion 16.

Le pignon 16 comporte par ailleurs une partie cylindrique 16b qui coopère avec l'engrenage 18 (ou avec le pignon inverseur 17).The pinion 16 further comprises a cylindrical portion 16b which cooperates with the gear 18 (or with the inverter pinion 17).

Comme cela est plus particulièrement visible à la figure 5, chaque support comporte une languette arrière 22. Cette languette forme un patin de frottement qui est maintenu radialement par une surface de butée 23 solidaire du corps de la sous-munition 6 (figure 4).As this is particularly visible in the figure 5 each support comprises a rear tongue 22. This tongue forms a friction pad which is held radially by an abutment surface 23 secured to the body of the submunition 6 ( figure 4 ).

Concrètement (voir figure 4) cette surface de butée 23 est une pièce rapportée sur un fond 24 solidaire de la sous-munition et qui ferme le logement des différentes pignons.Concretely (see figure 4 ) This abutment surface 23 is an insert on a bottom 24 secured to the submunition and which closes the housing of the different gears.

Lors de la rotation de chaque support 11 par rapport à son pivot 14 la languette 22 glisse sur la surface de butée 23 qui assure par ailleurs son maintien mécanique.During the rotation of each support 11 relative to its pivot 14 the tongue 22 slides on the abutment surface 23 which also ensures its mechanical retention.

Le dispositif selon l'invention présente un certain nombre d'avantages.The device according to the invention has a certain number of advantages.

Ainsi, bien que le plan aérodynamique de chaque gouverne 9 soit relativement large, les moyens d'entraînement mécaniques peuvent être logés très en arrière de la sous munition libérant ainsi un volume non négligeable pour la charge utile.Thus, although the aerodynamic plane of each rudder 9 is relatively wide, the mechanical drive means can be housed very behind the sub-munition thus releasing a significant volume for the payload.

Cela est rendu possible par l'articulation de chaque gouverne 9 au niveau d'un pivot 14 situé en avant du bord d'attaque (BA) de la gouverne alors que l'entraînement en rotation est assuré par une motorisation qui engrène sur une crémaillère voisine du bord de fuite (BF) de la gouverne.This is made possible by the articulation of each rudder 9 at a pivot 14 located in front of the leading edge (BA) of the rudder while the rotation drive is provided by a motor that meshes with a rack next to the trailing edge (BF) of the rudder.

Concrètement on a pu ainsi loger l'ensemble de la mécanique d'entraînement dans un boîtier arrière ayant une épaisseur de 20 à 25 mm pour un calibre de la sous-munition qui est voisin de 130 mm. Les dispositifs classiques peuvent occuper un volume au mieux équivalent mais ne présentent pas la robustesse du système proposé.Concretely it was thus able to accommodate all of the drive mechanism in a rear housing having a thickness of 20 to 25 mm for a submunition caliber which is close to 130 mm. Conventional devices can occupy a volume at best equivalent but do not have the robustness of the proposed system.

Il est possible à titre de variante de modifier les étages de pignonneries 26a, 26b pour assurer par exemple une commande par plans de gouvernes. On pourra par exemple n'utiliser que deux moto réducteurs, chacun entraînant deux gouvernes disposées dans le même plan.It is possible, as an alternative, to modify the stages of the bushings 26a, 26b to ensure, for example, a control by plane planes. For example, it will be possible to use only two geared motors, each driving two control surfaces arranged in the same plane.

Claims (6)

  1. An attitude control device for a piece of ammunition, or a submunition (6), comprising fins (9) integral with a body of the ammunition, the pivoting of each being controlled by a gear motor, so that the fins (9) are formed of flexible sheets able to be refolded by being wound around a rear part (12) of the ammunition body (6) and able to unwind to take up a substantially radial position with respect to the ammunition body, each fin (9) comprising a support (11) to carry the sheets and forming the surface of the fin (9), such support being hinged with respect to the ammunition body at a pivot (14) arranged to the fore of the fin surface, the support also being fitted with a rear rack (15) meshing on a pinion (16) driven by the attitude control gear motor.
  2. An attitude control device according to Claim 1, characterized in that the support (11) comprises a rear tongue (22) that is held radially by a stop surface (23) integral with the submunition body (6), the tongue (22) sliding on the stop surface (23) during the pivoting of the fin.
  3. An attitude control device according to one of Claims 1 or 2, characterized in that the rack (15) is conical.
  4. An attitude control device according to Claim 3, characterized in that the pinion (16) driving the rack (15) incorporates a conical part (16a) cooperating with the rack (15) and a cylindrical part (16b) cooperating with a gear train (18) driven by the gear motor.
  5. An attitude control device according to Claim 4, characterized in that the cylindrical part (16b) cooperates by means of an inverter pinion (17) with the gear train (18).
  6. An attitude control device according to Claim 5, characterized in that it comprises two gear motors with a short drive shaft carrying a gear train (18) to drive the pinion (16) and two gear motors having a long drive shaft carrying a gear train (18) to drive the pinion (16) by means of an inverter pinion (17).
EP08290062A 2007-01-31 2008-01-23 Device for controlling ammunition with deployable control surfaces Active EP1953494B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0700659A FR2911954B1 (en) 2007-01-31 2007-01-31 DEVICE FOR CONTROLLING AMMUNITION WITH DEPLOYABLE GOVERNMENTS

Publications (2)

Publication Number Publication Date
EP1953494A1 EP1953494A1 (en) 2008-08-06
EP1953494B1 true EP1953494B1 (en) 2010-05-26

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EP (1) EP1953494B1 (en)
AT (1) ATE469333T1 (en)
DE (1) DE602008001317D1 (en)
ES (1) ES2346721T3 (en)
FR (1) FR2911954B1 (en)

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WO2011058359A1 (en) * 2009-11-13 2011-05-19 Bae Systems Plc Guidance device
EP2322896A1 (en) * 2009-11-13 2011-05-18 BAE SYSTEMS plc Collar for a munition
IL207800B (en) 2010-08-25 2018-12-31 Bae Systems Rokar Int Ltd Control apparatus for guiding a cannon shell in flight and method of using same
CN112093032B (en) * 2020-11-05 2021-02-09 成都云鼎智控科技有限公司 Unmanned vehicles flight control system and duct fan installation and telex interface module
CN112093033B (en) * 2020-11-05 2021-02-09 成都云鼎智控科技有限公司 Unmanned vehicles flight control system
CN112027064B (en) * 2020-11-06 2021-07-30 成都云鼎智控科技有限公司 Unmanned vehicles flight control system and steering wheel orientation module
CN112141349B (en) * 2020-11-27 2021-02-26 成都云鼎智控科技有限公司 Control system of unmanned aerial vehicle engine

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US4296895A (en) * 1979-01-15 1981-10-27 General Dynamics Corporation Fin erection mechanism
FR2623898B1 (en) 1987-11-26 1990-03-23 France Etat Armement DEVICE FOR DEPLOYING A PROJECTILE FIN
SE460738B (en) 1988-03-16 1989-11-13 Bofors Ab BEFORE MISSILES AND OTHER PROJECTILES INTENDED FOR FALLABLE WINGS
DE4025515C2 (en) 1990-08-11 1994-05-11 Deutsche Aerospace Wing for missiles launching from a tube
US5505408A (en) * 1993-10-19 1996-04-09 Versatron Corporation Differential yoke-aerofin thrust vector control system
FR2768809B1 (en) 1997-09-24 1999-10-15 Giat Ind Sa LARGE CALIBER LONG RANGE FIELD ARTILLERY PROJECTILE
FR2846080B1 (en) 2002-10-17 2007-05-25 Giat Ind Sa DEVICE FOR DEPLOYING AND TRAINING PROJECTILE GOVERNMENTS
FR2864613B1 (en) 2003-12-31 2006-03-17 Giat Ind Sa DEVICE FOR DEPLOYING AND DRIVING GOVERNS OF A PROJECTILE
DE102006022248B3 (en) * 2006-05-12 2007-11-08 Lfk-Lenkflugkörpersysteme Gmbh Retaining device on wrapped wings of flying object, allowing reliable release of wings into working position, comprises controlled release holder on one wing and cooperating fixtures on others

Also Published As

Publication number Publication date
ES2346721T3 (en) 2010-10-19
FR2911954B1 (en) 2009-04-24
EP1953494A1 (en) 2008-08-06
ATE469333T1 (en) 2010-06-15
FR2911954A1 (en) 2008-08-01
DE602008001317D1 (en) 2010-07-08

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