EP1548392A1 - Device for the deployment of the vanes of a projectile - Google Patents

Device for the deployment of the vanes of a projectile Download PDF

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Publication number
EP1548392A1
EP1548392A1 EP04292926A EP04292926A EP1548392A1 EP 1548392 A1 EP1548392 A1 EP 1548392A1 EP 04292926 A EP04292926 A EP 04292926A EP 04292926 A EP04292926 A EP 04292926A EP 1548392 A1 EP1548392 A1 EP 1548392A1
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EP
European Patent Office
Prior art keywords
star
projectile
fins
deployment device
inertial
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.)
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Application number
EP04292926A
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German (de)
French (fr)
Inventor
Grégoire Agnelot
Jean-François Pierrot
Vincent Cady
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Nexter Munitions SA
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Giat Industries SA
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Filing date
Publication date
Application filed by Giat Industries SA filed Critical Giat Industries SA
Publication of EP1548392A1 publication Critical patent/EP1548392A1/en
Withdrawn legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • 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

Definitions

  • the technical field of the invention is that of devices ensuring the deployment of fins stabilization for projectiles.
  • the fins deployment devices are well known. These devices use for example the pressure of the aerodynamic flow received by the fins (solution described by FR2721702) or a borrowing of propellant gases of the weapon (solution described by US4702436).
  • Gas-based solutions have reliability insufficient because of the highly erosive nature of the gases propulsion.
  • the fin deployment device according to the invention can be implemented to control the deployment of a tail stabilizer rear.
  • This device may also, given its compactness, to be used to deploy duck rudders carried by a front part of a projectile.
  • the subject of the invention is a device for deployment of projectile fins, comprising a lock means ensuring the simultaneous immobilization of all the fins in the folded position, device characterized in that it comprises an actuator releasing the medium lock when firing, actuator comprising a inertial flyweight.
  • the lock means comprises a star pivotally mounted relative to an axis of the projectile, star with arms and each arm having an end carrying a hook engaged in a notch of a fin to ensure its immobilization.
  • the star will be advantageously pivotally mounted against the action of a spring means having the effect of clearing the hooks of their notches to ensure the release of fins.
  • the star may be immobilized in rotation by at least a finger integral with the inertial flyweight.
  • the inertial flyweight can be attached to a tray carrying a finger for each fin.
  • the device has a braking means to slow down the pivoting of the star.
  • This braking means may be constituted by a disk of friction interposed between the star and the body of the projectile.
  • the star can be held in support against the disc friction by an elastic cup.
  • the device may include means for locking of the flyweight relative to the projectile body after its recoil under the effect of shooting inertia.
  • Figures 1 and 2 show in section a front part of a projectile 1 carrying four duck rudders 2a, 2b, 2c 2d. This projectile is intended to fly along the AV arrow shown in Figure 1.
  • the control surfaces 2 provide a stabilization of the projectile.
  • Each rudder is pivotally mounted about an axis 3 integral with the projectile.
  • a spiral spring 4 is mounted around of each axis 3. It is supported on one side on the body of projectile and the other on a rim of the fin. This spring 4 has the effect of rotating the fin to bring it into the deployed position.
  • the four fins are held in their position folded, against the action of the springs 4, thanks to a means lock 5.
  • the lock means 5 comprises a star 6 which is mounted pivoting on a cylindrical support 7 which is coaxial with axis 8 of the projectile 1.
  • the star 6 has four arms 6a, 6b, 6c and 6d and each arm carries at its end a hook 9a, 9b, 9c or 9d which is engaged in a notch 10a, 10b, 10c or 10d of a fin for ensure its immobilization in the folded position.
  • a spiral spring 11 is disposed in a housing 21 of the star 6. It is interposed between the star 6 and the support 7. This spring is in the banded condition when the device is in the folded fins position shown in Figures 1 and 2. It has the effect of turn the star 6 counterclockwise shows in Figure 2, ie in the sense that clears the hooks 9a, 9b, 9c and 9d out of the notches 10a, 10b, 10c and 10d.
  • a friction disk 19 made of a thermoplastic material or elastomer is interposed between the star 6 and the body of the projectile 1.
  • a pressing force between the disc of friction 19, the star 6 and the body of the projectile 1 is provided by a cup 20 of elastic material which is disposed in the housing 21 of the star 6.
  • the cup 20 is locked axially by an elastic ring 22 positioned on axis 7.
  • the axial pressing force is ensured by the deformation elastic of the cup after mounting the ring 22.
  • the cup 20 has a V-shaped light (not visible on the figures) which allows to release the connection of the spring spiral 11 and star 6.
  • the cup also ensures the protection of the spring 11 and it contains a lubricating agent for this latest.
  • the friction disc 19 has the function of ensuring a braking of the rotation movement of the star 6. Braking can be adjusted by modifying the pressure effort given by the cup 20.
  • the star 6 is immobilized against the action of the spring 11 by a plate 12 carrying four fingers cylindrical 13a, 13b, 13c and 13d (see Figure 2).
  • Each finger 13 is in contact with one of the arms of the star 6.
  • the plate 12 is integral with an inertial flyweight 14 which is slidably mounted in a bore 15 of a portion 1a of the projectile body 1 (the connecting means between this part 1a and the rest of the projectile body are not shown in the figures).
  • the weight 14 is guided in translation by a radial pin 16 which cooperates with two grooves 18 of the bore 15 (see also Figure 3).
  • the weight 14 constitutes an actuator capable of release the lock means 5 when firing.
  • the weight is locked on an elastic ring 23 which is disposed in a groove in the bottom of the bore 15. effect it has a groove 24 inside which penetrates the ring 23.
  • the fins are released only when the projectile is out of the tube of the weapon (a delay of 20 milliseconds is sufficient). This avoids any contact between the fins and the inner wall of the barrel of the weapon.
  • FIGS 3 and 4 show the device in the deployed position.
  • Each fin 2 is immobilized in position deployed by a leaf spring 25 which cooperates with a heel 26 carried by the fin.
  • the invention has been described here applied to deployment of duck wings arranged at a front portion of a projectile. It would of course be possible to put it in works for a rear stabilizer stabilizer.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Abstract

The deployment mechanism for the fins (2a, 2b) of a projectile (1), which are held in their retracted positions by a single lock (5), has an actuator in the form of an inertial weight (14) that releases the lock when the projectile is fired. The lock is in the form of a pivoting star-wheel (6) with hooks (9a, 9b) on the ends of its arms to engage with slots (10b) in the retracted fins, with a spring that causes the star wheel to rotate and remove the hooks from the slots when it is released by the inertial weight, allowing the fins to deploy.

Description

Le domaine technique de l'invention est celui des dispositifs assurant le déploiement d'ailettes de stabilisation pour projectiles.The technical field of the invention is that of devices ensuring the deployment of fins stabilization for projectiles.

Les dispositifs de déploiement d'ailettes sont bien connus. Ces dispositifs utilisent par exemple la pression de l'écoulement aérodynamique reçu par les ailettes (solution décrite par FR2721702) ou bien un emprunt des gaz propulsifs de l'arme (solution décrite par US4702436).The fins deployment devices are well known. These devices use for example the pressure of the aerodynamic flow received by the fins (solution described by FR2721702) or a borrowing of propellant gases of the weapon (solution described by US4702436).

Les solutions à emprunt de gaz ont une fiabilité insuffisante en raison du caractère fortement érosif des gaz propulsifs.Gas-based solutions have reliability insufficient because of the highly erosive nature of the gases propulsion.

Les solutions utilisant l'écoulement aérodynamique peuvent conduire à des dissymétries d'ouverture des ailettes ce qui nuit à la stabilité du vol du projectile.Solutions using aerodynamic flow can lead to dissymmetries of opening of the fins which hampers the stability of the flight of the projectile.

On connaít également (par exemple par la demande de brevet US6446906) des dispositifs de déploiement mettant en oeuvre un actionneur utilisant une énergie embarquée (électrique ou pyrotechnique). Cet actionneur commande sur trajectoire à un instant donné la libération des ailettes.We also know (for example by the request of patent US6446906) deployment devices implementing an actuator using an embedded energy (electric or pyrotechnic). This actuator controls on trajectory at a given moment the release of the fins.

Ces solutions sont complexes et encombrantes et elles imposent la mise en place de moyens électroniques de commande de l'actionneur ainsi qu'éventuellement de moyens de sécurité pour éviter un déclenchement intempestif d'un actionneur pyrotechnique.These solutions are complex and cumbersome and they impose the establishment of electronic control means actuator as well as possibly security means to avoid accidental tripping of an actuator pyrotechnic.

C'est le but de l'invention que de proposer un dispositif de déploiement d'ailette fiable et peu encombrant.It is the object of the invention to provide a device reliable and space saving blade deployment.

Le dispositif de déploiement d'ailette selon l'invention peut être mis en oeuvre pour commander le déploiement d'un empennage de stabilisation arrière.The fin deployment device according to the invention can be implemented to control the deployment of a tail stabilizer rear.

Ce dispositif peut également, compte tenu de sa compacité, être utilisé pour déployer des gouvernes canard portées par une partie avant d'un projectile.This device may also, given its compactness, to be used to deploy duck rudders carried by a front part of a projectile.

Ainsi l'invention a pour objet un dispositif de déploiement d'ailettes pour projectile, dispositif comprenant un moyen verrou assurant l'immobilisation simultanée de toutes les ailettes en position repliée, dispositif caractérisé en ce qu'il comporte un actionneur libérant le moyen verrou lors du tir, actionneur comprenant une masselotte inertielle.Thus, the subject of the invention is a device for deployment of projectile fins, comprising a lock means ensuring the simultaneous immobilization of all the fins in the folded position, device characterized in that it comprises an actuator releasing the medium lock when firing, actuator comprising a inertial flyweight.

Selon un mode particulier de réalisation, le moyen verrou comprend une étoile montée pivotante par rapport à un axe du projectile, étoile comportant des bras et chaque bras comportant une extrémité portant un crochet engagé dans une encoche d'une ailette pour assurer son immobilisation.According to a particular embodiment, the lock means comprises a star pivotally mounted relative to an axis of the projectile, star with arms and each arm having an end carrying a hook engaged in a notch of a fin to ensure its immobilization.

L'étoile sera avantageusement montée pivotante contre l'action d'un moyen ressort ayant pour effet de dégager les crochets de leurs encoches pour assurer la libération des ailettes.The star will be advantageously pivotally mounted against the action of a spring means having the effect of clearing the hooks of their notches to ensure the release of fins.

L'étoile pourra être immobilisée en rotation par au moins un doigt solidaire de la masselotte inertielle.The star may be immobilized in rotation by at least a finger integral with the inertial flyweight.

La masselotte inertielle pourra être solidaire d'un plateau portant un doigt pour chaque ailette.The inertial flyweight can be attached to a tray carrying a finger for each fin.

Selon un mode particulier de réalisation, le dispositif comporte un moyen de freinage permettant de ralentir le pivotement de l'étoile.According to a particular embodiment, the device has a braking means to slow down the pivoting of the star.

Ce moyen de freinage pourra être constitué par un disque de friction interposé entre l'étoile et le corps du projectile.This braking means may be constituted by a disk of friction interposed between the star and the body of the projectile.

L'étoile pourra être maintenue en appui contre le disque de friction par une coupelle élastique.The star can be held in support against the disc friction by an elastic cup.

Selon une autre caractéristique de l'invention, le dispositif pourra comporter un moyen assurant le verrouillage de la masselotte par rapport au corps de projectile après son recul sous l'effet de l'inertie de tir.According to another characteristic of the invention, the device may include means for locking of the flyweight relative to the projectile body after its recoil under the effect of shooting inertia.

L'invention sera mieux comprise à la lecture de la description qui va suivre d'un mode particulier de réalisation, description faite en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue partielle en coupe longitudinale d'une partie avant de projectile portant des gouvernes canard déployées par un dispositif selon l'invention, le dispositif étant représenté en position repliée,
  • la figure 2 est une vue en coupe transversale de e même dispositif, coupe réalisée suivant le plan dont la trace AA est visible à la figure 1,
  • la figure 3 est une vue analogue à la figure 1, le dispositif étant représenté en position déployée,
  • la figure 4 est une vue en coupe transversale du dispositif en position déployée, coupe réalisée suivant le plan dont la trace BB est visible à la figure 3.
The invention will be better understood on reading the following description of a particular embodiment, a description given with reference to the appended drawings in which:
  • FIG. 1 is a partial view in longitudinal section of a projectile front portion carrying duck rudders deployed by a device according to the invention, the device being represented in the folded position,
  • FIG. 2 is a cross-sectional view of the same device, cut along the plane whose trace AA is visible in FIG.
  • FIG. 3 is a view similar to FIG. 1, the device being shown in the deployed position,
  • FIG. 4 is a cross-sectional view of the device in the deployed position, cut along the plane whose trace BB is visible in FIG.

Pour des raisons d'encombrement, les différentes figures ne sont pas toutes à la même échelle.For reasons of space, the different figures are not all on the same scale.

Les figures 1 et 2 montrent en coupe une partie avant d'un projectile 1 portant quatre gouvernes canard 2a, 2b, 2c 2d. Ce projectile est destiné à voler suivant la flèche AV représentée sur la figure 1. Les gouvernes 2 assurent une stabilisation du projectile.Figures 1 and 2 show in section a front part of a projectile 1 carrying four duck rudders 2a, 2b, 2c 2d. This projectile is intended to fly along the AV arrow shown in Figure 1. The control surfaces 2 provide a stabilization of the projectile.

Chaque gouverne est montée pivotante autour d'un axe 3 solidaire du projectile. Un ressort spiral 4 est monté autour de chaque axe 3. Il prend appui d'un côté sur le corps de projectile et de l'autre sur un rebord de l'ailette. Ce ressort 4 a pour effet de faire pivoter l'ailette pour l'amener en position déployée.Each rudder is pivotally mounted about an axis 3 integral with the projectile. A spiral spring 4 is mounted around of each axis 3. It is supported on one side on the body of projectile and the other on a rim of the fin. This spring 4 has the effect of rotating the fin to bring it into the deployed position.

Les quatre ailettes sont maintenues dans leur position repliée, contre l'action des ressorts 4, grâce à un moyen verrou 5.The four fins are held in their position folded, against the action of the springs 4, thanks to a means lock 5.

Le moyen verrou 5 comprend une étoile 6 qui est montée pivotante sur un support cylindrique 7 qui est coaxial à l'axe 8 du projectile 1.The lock means 5 comprises a star 6 which is mounted pivoting on a cylindrical support 7 which is coaxial with axis 8 of the projectile 1.

L'étoile 6 comporte quatre bras 6a,6b,6c et 6d et chaque bras porte à son extrémité un crochet 9a,9b,9c ou 9d qui est engagé dans une encoche 10a,10b,10c ou 10d d'une ailette pour assurer son immobilisation en position repliée.The star 6 has four arms 6a, 6b, 6c and 6d and each arm carries at its end a hook 9a, 9b, 9c or 9d which is engaged in a notch 10a, 10b, 10c or 10d of a fin for ensure its immobilization in the folded position.

Un ressort spiral 11 est disposé dans un logement 21 de l'étoile 6. Il est interposé entre l'étoile 6 et le support cylindrique 7. Ce ressort est à l'état bandé lorsque le dispositif se trouve dans la position ailettes repliées représentée aux figures 1 et 2. Il a pour effet de faire tourner l'étoile 6 dans le sens contraire aux aiguilles d'une montre sur la figure 2, c'est à dire dans le sens qui dégage les crochets 9a,9b,9c et 9d hors des encoches 10a, 10b, 10c et 10d.A spiral spring 11 is disposed in a housing 21 of the star 6. It is interposed between the star 6 and the support 7. This spring is in the banded condition when the device is in the folded fins position shown in Figures 1 and 2. It has the effect of turn the star 6 counterclockwise shows in Figure 2, ie in the sense that clears the hooks 9a, 9b, 9c and 9d out of the notches 10a, 10b, 10c and 10d.

Un disque de friction 19 en un matériau thermoplastique ou en élastomère est interposé entre l'étoile 6 et le corps du projectile 1. Un effort presseur entre le disque de friction 19, l'étoile 6 et le corps du projectile 1 est assuré par une coupelle 20 en matériau élastique qui est disposée dans le logement 21 de l'étoile 6. La coupelle 20 est bloquée axialement par un anneau élastique 22 positionné sur l'axe 7.A friction disk 19 made of a thermoplastic material or elastomer is interposed between the star 6 and the body of the projectile 1. A pressing force between the disc of friction 19, the star 6 and the body of the projectile 1 is provided by a cup 20 of elastic material which is disposed in the housing 21 of the star 6. The cup 20 is locked axially by an elastic ring 22 positioned on axis 7.

L'effort presseur axial est assuré par la déformation élastique de la coupelle après montage de l'anneau 22.The axial pressing force is ensured by the deformation elastic of the cup after mounting the ring 22.

La coupelle 20 comporte une lumière en V (non visible sur les figures) qui permet de dégager la liaison du ressort spiral 11 et de l'étoile 6.The cup 20 has a V-shaped light (not visible on the figures) which allows to release the connection of the spring spiral 11 and star 6.

La coupelle permet également d'assurer la protection du ressort 11 et elle contient un agent lubrifiant pour ce dernier.The cup also ensures the protection of the spring 11 and it contains a lubricating agent for this latest.

Le disque de friction 19 a pour fonction d'assurer un freinage du mouvement de rotation de l'étoile 6. Le freinage peut être réglé en modifiant l'effort presseur donné par la coupelle 20. L'étoile 6 se trouve immobilisée contre l'action du ressort 11 par un plateau 12 portant quatre doigts cylindriques 13a,13b,13c et 13d (voir figure 2). The friction disc 19 has the function of ensuring a braking of the rotation movement of the star 6. Braking can be adjusted by modifying the pressure effort given by the cup 20. The star 6 is immobilized against the action of the spring 11 by a plate 12 carrying four fingers cylindrical 13a, 13b, 13c and 13d (see Figure 2).

Chaque doigt 13 est en contact avec un des bras de l'étoile 6.Each finger 13 is in contact with one of the arms of the star 6.

Un seul doigt serait suffisant pour assurer le maintien de l'étoile. Cependant prévoir autant de doigts 13 que de bras de l'étoile 6 permet de répartir les efforts de matage résultant de l'action du ressort 11. Il en résulte une meilleure symétrie du dispositif ce qui évite tout coincement lors du déplacement du plateau 12.One finger would be enough to maintain of the star. However, provide as many fingers 13 as arm of the star 6 helps to spread the efforts of matting resulting from the action of spring 11. This results in a better symmetry of the device which avoids any jamming when moving the tray 12.

Le plateau 12 est solidaire d'une masselotte inertielle 14 qui est montée coulissante dans un alésage 15 d'une partie 1a du corps de projectile 1 (les moyens de liaison entre cette partie 1a et le reste du corps de projectile ne sont pas représentés sur les figures).The plate 12 is integral with an inertial flyweight 14 which is slidably mounted in a bore 15 of a portion 1a of the projectile body 1 (the connecting means between this part 1a and the rest of the projectile body are not not shown in the figures).

La masselotte 14 est guidée en translation par une goupille radiale 16 qui coopère avec deux rainures 18 de l'alésage 15 (voir aussi figure 3).The weight 14 is guided in translation by a radial pin 16 which cooperates with two grooves 18 of the bore 15 (see also Figure 3).

Dans la position repliée des figures 1 et 2, la masselotte 14 est immobilisée en translation par un anneau cisaillable 17 qui se loge dans une gorge annulaire de l'alésage 15.In the folded position of Figures 1 and 2, the weight 14 is immobilized in translation by a ring shear 17 which is housed in an annular groove of the bore 15.

La masselotte 14 constitue un actionneur susceptible de libérer le moyen verrou 5 lors du tir.The weight 14 constitutes an actuator capable of release the lock means 5 when firing.

Le fonctionnement du dispositif est le suivant (voir figures 3 et 4).The operation of the device is as follows (see Figures 3 and 4).

Lors du tir du projectile (direction de tir donnée par la flèche AV), des efforts d'inertie s'exercent sur la masselotte 14. Ces efforts tendent à la faire reculer à l'intérieur de l'alésage 15. Ils provoquent le cisaillement de l'anneau 17. La masselotte 14 recule entraínant le plateau 12 portant les doigts 13a,13b,13c et 13d.When shooting the projectile (firing direction given by the arrow AV), inertial efforts are exerted on the These efforts tend to reduce it to inside the bore 15. They cause the shear of the ring 17. The feeder 14 moves back causing the plateau 12 carrying the fingers 13a, 13b, 13c and 13d.

La masselotte se verrouille sur un jonc élastique 23 qui est disposé dans une gorge du fond de l'alésage 15. A cet effet elle comporte une gorge 24 à l'intérieur de laquelle pénètre le jonc 23. The weight is locked on an elastic ring 23 which is disposed in a groove in the bottom of the bore 15. effect it has a groove 24 inside which penetrates the ring 23.

Ce verrouillage en position arrière de la masselotte 14 ainsi que du plateau 12 qu'elle porte permet d'empêcher les oscillations de la masselotte 14 lors de la phase canon. On évite ainsi toute perturbation lors de la libération de l'étoile 6 par les doigts 13a, 13b, 13c et 13d.This locking in the back position of the weight 14 as well as the plate 12 which it carries makes it possible to oscillations of the flyweight 14 during the gun phase. We avoids any disturbance during the release of the star 6 by the fingers 13a, 13b, 13c and 13d.

Une fois l'étoile 6 libérée, elle pivote, entraínée par son ressort 11.Once the star 6 released, it pivots, driven by its spring 11.

Grâce au freinage assuré par le disque de friction 19, les ailettes ne sont libérées que lorsque le projectile est sorti du tube de l'arme (une temporisation de l'ordre de 20 millisecondes est suffisante). On évite ainsi tout contact entre les ailettes et la paroi interne du tube de l'arme.Thanks to the braking provided by the friction disc 19, the fins are released only when the projectile is out of the tube of the weapon (a delay of 20 milliseconds is sufficient). This avoids any contact between the fins and the inner wall of the barrel of the weapon.

La libération des quatre ailettes 2a,2b,2c et 2d se produit d'une façon simultanéeThe release of the four fins 2a, 2b, 2c and 2d is produced simultaneously

Les figures 3 et 4 montrent le dispositif dans la position déployée. Chaque ailette 2 se trouve immobilisée en position déployée par une lame ressort 25 qui coopère avec un talon 26 porté par l'ailette.Figures 3 and 4 show the device in the deployed position. Each fin 2 is immobilized in position deployed by a leaf spring 25 which cooperates with a heel 26 carried by the fin.

Différentes variantes sont possibles sans sortir du cadre de l'invention. Il est bien entendu possible de définir un dispositif de déploiement pour un nombre d'ailettes différent.Different variants are possible without going outside the box of the invention. It is of course possible to define a deployment device for a number of fins different.

L'invention a été décrite ici appliquée au déploiement d'ailettes canard disposées au niveau d'une partie avant d'un projectile. Il serait bien entendu possible de la mettre en oeuvre pour un empennage de stabilisation arrière.The invention has been described here applied to deployment of duck wings arranged at a front portion of a projectile. It would of course be possible to put it in works for a rear stabilizer stabilizer.

Claims (9)

Dispositif de déploiement d'ailettes pour projectile (1), dispositif comprenant un moyen verrou (5) assurant l'immobilisation simultanée de toutes les ailettes (2a,2b,2c,2d) en position repliée, dispositif caractérisé en ce qu'il comporte un actionneur libérant le moyen verrou (5) lors du tir, actionneur comprenant une masselotte inertielle (14).Device for deploying projectile fins (1), device comprising a locking means (5) ensuring the simultaneous immobilization of all the fins (2a, 2b, 2c, 2d) in the folded position, characterized in that it comprises an actuator releasing the lock means (5) during firing, the actuator comprising an inertial flyweight (14). Dispositif de déploiement d'ailettes selon la revendication 1, dispositif caractérisé en ce que le moyen verrou (5) comprend une étoile (6) montée pivotante par rapport à un axe (8) du projectile (1), étoile comportant des bras (6a, 6b, 6c, 6d) et chaque bras comportant une extrémité portant un crochet (9a,9b,9c,9d) engagé dans une encoche (10a,10b,10c,10d) d'une ailette (2a,2b,2c,2d) pour assurer son immobilisation.Fan deployment device according to claim 1, characterized in that the locking means (5) comprises a star (6) pivotally mounted relative to an axis (8) of the projectile (1), a star comprising arms (6a , 6b, 6c, 6d) and each arm having an end carrying a hook (9a, 9b, 9c, 9d) engaged in a notch (10a, 10b, 10c, 10d) of a fin (2a, 2b, 2c, 2d ) to ensure its immobilization. Dispositif de déploiement d'ailettes selon la revendication 2, dispositif caractérisé en ce que l'étoile (6) est montée pivotante contre l'action d'un moyen ressort (11) ayant pour effet de dégager les crochets (9a,9b,9c,9d) de leurs encoches (10a,10b,10c,10d) pour assurer la libération des ailettes (2a,2b,2c,2d).Fan deployment device according to claim 2, characterized in that the star (6) is pivotally mounted against the action of a spring means (11) having the effect of releasing the hooks (9a, 9b, 9c 9d) of their notches (10a, 10b, 10c, 10d) to ensure the release of the fins (2a, 2b, 2c, 2d). Dispositif de déploiement d'ailettes selon la revendication 3, dispositif caractérisé en ce que l'étoile (6) est immobilisée en rotation par au moins un doigt (13a,13b,13c,13d) solidaire de la masselotte inertielle (14).Wing deployment device according to claim 3, characterized in that the star (6) is immobilized in rotation by at least one finger (13a, 13b, 13c, 13d) integral with the inertial flyweight (14). Dispositif de déploiement d'ailettes selon la revendication 4, dispositif caractérisé en ce que la masselotte inertielle (14) est solidaire d'un plateau (12) portant un doigt (13a,13b,13c,13d) pour chaque ailette.Wing deployment device according to claim 4, characterized in that the inertial flyweight (14) is integral with a plate (12) carrying a finger (13a, 13b, 13c, 13d) for each fin. Dispositif de déploiement d'ailettes selon une des revendications 2 à 5, dispositif caractérisé en ce qu'il comporte un moyen de freinage permettant de ralentir le pivotement de l'étoile (6).Wing deployment device according to one of claims 2 to 5, characterized in that it comprises a braking means for slowing the pivoting of the star (6). Dispositif de déploiement d'ailettes selon la revendication 6, dispositif caractérisé en ce que le moyen de freinage est constitué par un disque de friction (19) interposé entre l'étoile (6) et le corps du projectile (1).Wing deployment device according to claim 6, characterized in that the braking means is constituted by a friction disc (19) interposed between the star (6) and the body of the projectile (1). Dispositif de déploiement d'ailettes selon la revendication 7, dispositif caractérisé en ce que l'étoile (6) est maintenue en appui contre le disque de friction (19) par une coupelle élastique (20).Fan deployment device according to claim 7, characterized in that the star (6) is held in abutment against the friction disc (19) by an elastic cup (20). Dispositif de déploiement d'ailettes selon une des revendications 1 à 8, dispositif caractérisé en ce qu'il comporte un moyen (23) assurant le verrouillage de la masselotte (14) par rapport au corps de projectile (1) après son recul sous l'effet de l'inertie de tir.Device for deploying fins according to one of claims 1 to 8, characterized in that it comprises means (23) for locking the weight (14) relative to the projectile body (1) after its retraction under the effect of shooting inertia.
EP04292926A 2003-12-24 2004-12-09 Device for the deployment of the vanes of a projectile Withdrawn EP1548392A1 (en)

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FR0315486 2003-12-24
FR0315486A FR2864612B1 (en) 2003-12-24 2003-12-24 DEVICE FOR DEPLOYING THE FINS OF A PROJECTILE

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CN109186370A (en) * 2018-07-26 2019-01-11 重庆长安工业(集团)有限责任公司 A kind of folded surface unfolding mechanism
EP3543640A3 (en) * 2018-03-21 2020-01-08 Diehl Defence GmbH & Co. KG Projectile with deployable fins that are releasably held in stowed position by a common latch element rotatable around the longitudinal axis

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FR2955653A1 (en) * 2010-01-28 2011-07-29 Nexter Munitions DEVICE FOR SIMULTANEOUS DEPLOYMENT OF GOVERNMENTS OF A PROJECTILE
EP2354755A1 (en) * 2010-01-28 2011-08-10 Nexter Munitions Device for simultaneously deploying control surfaces of a projectile
US8592737B2 (en) 2010-01-28 2013-11-26 Nexter Munitions Device for simultaneous deployment of the control surfaces of a projectile
EP3543640A3 (en) * 2018-03-21 2020-01-08 Diehl Defence GmbH & Co. KG Projectile with deployable fins that are releasably held in stowed position by a common latch element rotatable around the longitudinal axis
CN109186370A (en) * 2018-07-26 2019-01-11 重庆长安工业(集团)有限责任公司 A kind of folded surface unfolding mechanism

Also Published As

Publication number Publication date
FR2864612A1 (en) 2005-07-01
FR2864612B1 (en) 2007-11-23

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