EP2354755B1 - Device for simultaneously deploying control surfaces of a projectile - Google Patents

Device for simultaneously deploying control surfaces of a projectile Download PDF

Info

Publication number
EP2354755B1
EP2354755B1 EP11290029A EP11290029A EP2354755B1 EP 2354755 B1 EP2354755 B1 EP 2354755B1 EP 11290029 A EP11290029 A EP 11290029A EP 11290029 A EP11290029 A EP 11290029A EP 2354755 B1 EP2354755 B1 EP 2354755B1
Authority
EP
European Patent Office
Prior art keywords
projectile
control surfaces
deployment device
ferrule
axis
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.)
Active
Application number
EP11290029A
Other languages
German (de)
French (fr)
Other versions
EP2354755A1 (en
Inventor
Geoffroy Deschatre
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.)
Nexter Munitions SA
Original Assignee
Nexter Munitions SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nexter Munitions SA filed Critical Nexter Munitions SA
Priority to PL11290029T priority Critical patent/PL2354755T3/en
Publication of EP2354755A1 publication Critical patent/EP2354755A1/en
Application granted granted Critical
Publication of EP2354755B1 publication Critical patent/EP2354755B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • 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 deployment devices projectile control surfaces.
  • control surfaces In order to bring greater precision to modern ballistic or propelled projectiles, these are equipped with control surfaces to correct the trajectory or stabilize the projectile. These control surfaces are driven by electric motors. Given the congestion represented by the control surfaces, these are generally contained in the body of the projectile during the phases of handling and installation in a weapon tube and during the internal ballistic phase. The control surfaces are then deployed in flight.
  • the patent EP-1550837 proposes to deploy the control surfaces to resort to springs equipping each control surfaces individually.
  • This device has a major disadvantage. In order not to compromise the stability of the projectile, it is essential that the deployment of all control surfaces is simultaneous, but this device does not provide all the necessary guarantees because it has the disadvantage that the springs have effects independent of each other. other. As a result of the differences in elasticity or other mechanical characteristics of the springs may cause a deferred exit of the control surfaces relative to each other.
  • DE-3838735 describes a device for simultaneous deployment of fins.
  • this device requires a single sliding element having a toothing on its periphery and meshing with the gears of the base of the fins.
  • the invention proposes to provide a solution ensuring simultaneous deployment of all the control surfaces.
  • the deployment energy is provided by a single spring which simultaneously slides racks allowing the simultaneous deployment of the control surfaces while allowing them once deployed to be pivoted on themselves, by the control of an engine, to ensure the steering of the projectile.
  • the invention relates to a device for deploying control surfaces of a projectile for which each rudder is intended to be pivoted by a motor after deployment to provide steering, each rudder being held inside the projectile and deployed to the outside the projectile by the expansion of an elastic means, each rudder unfolding by rotation relative to a steering support and a transverse axis of deployment to the axis of the projectile.
  • This device for deploying control surfaces is characterized in that the elastic means is a common means which ensures the deployment of all the control surfaces, the expansion of the elastic means generating a thrust force directed along the axis of the projectile and exerting on a thrust plate which transmits the thrust force to as many sliders as there are control surfaces to be deployed, each slide cooperating without sliding with a complementary profile integral with a base of the rudder to rotate it by relative to its support and a first releasable locking means also ensuring the retention of the elastic means in the compressed position.
  • the first locking means is constituted by a substantially cylindrical ferrule which separates the thrust plate from the sliders when the resilient means is compressed, the ferrule comprising pins on which abutment radial arms carried by the thrust plate, the ferrule being pivotable along the axis of the projectile to release the thrust plate and cause the relaxation of the elastic means, the radial arms then pushing the slides.
  • the device comprises a second releasable locking means which keeps the control surfaces in the folded position.
  • the device comprises a third locking means maintaining the control surfaces in the deployed position.
  • the ferrule comprises an internal toothing cooperating with a second pinion driven by a motor to allow the pivoting of the ferrule and the unlocking of the elastic means.
  • the second locking means comprises fingers integral with the ferrule, each finger engaging in a longitudinal groove of the slide, the fingers being disengaged from their grooves during the pivoting of the ferrule.
  • the third locking means is constituted for each rudder by at least one ball stop engaging in a recess of the slide when the control surfaces are deployed.
  • the slide is a rack which cooperates with a complementary profile formed by a first toothed gear integral with the base of the rudder.
  • the thrust plate which is slidably mounted on an axis coaxial with the projectile, may comprise a tooth which will ensure its guidance on this axis, a tooth which circulates in a longitudinal groove which ends with a helicoidal portion, the thrust plate pivoting thus partially around the axis at the end of its axial displacement so that each arm is moved away from the slide it pushed.
  • a projectile 1 is equipped with rudders 2a, 2b, 2c and 2d shown deployed and arranged at a front part of the projectile 1.
  • rudders 2a, 2b, 2c and 2d shown deployed and arranged at a front part of the projectile 1.
  • the deployment device of the control surfaces 4 is contained in the front part of the projectile 1 and is therefore not visible in the drawing in its entirety. In the folded position, the control surfaces 2a to 2d are inserted into the slots 3 (configuration not shown in the figure).
  • the deployment device comprises a body 5 which houses the control surfaces 2a to 2d in the folded position (only two control surfaces are visible on the figure 2 ).
  • the base of each rudder 2a to 2d comprises a toothing forming a pinion 6.
  • This pinion base 6 is traversed by an axis 7 integral with a support 8.
  • each support 8 is intended to be pivoted along an axis perpendicular to the axis of the projectile to enable control. This pivoting is provided by a motor (not shown).
  • the pinion 6 meshes with a toothed slider (also called rack 9) which slides in a groove of the body 5.
  • the deployment device 4 comprises in its foremost part a cover 10 (only one sector of the cover 10 is shown) integral with the body 5.
  • This cover 10 comprises in its center a housing accommodating the end of a compressed elastic means which is here a spring 11 with helical turns.
  • a first end of the spring 11 is supported on a cross-shaped thrust plate 12 which has radial arms (as many radial arms as there are racks 9).
  • the arms of the thrust plate are each supported on a lug 13a to 13d integral with a ferrule 13 (the lug 13c is not visible on the figure 2 because masked by the hood portion 10).
  • the shell 13 is more particularly visible on the figure 8 . It is substantially cylindrical and has a ring gear with internal teeth 14 on its inner periphery. This ring gear 14 meshes with a pinion 15 driven by a motor (not shown).
  • the lugs 13a, 13b, 13c and 13d are configured in the form of flat tabs which extend radially inwardly of the shell 13 and which are regularly distributed angularly.
  • the control surfaces 2a to 2d are folded and the lugs 13a to 13d of the shell 13 separate the racks 9 from the arms of the thrust plate 12. In this way the racks 9 do not undergo the force generated by the spring 11 thus avoiding the deployment of the control surfaces 2a to 2d.
  • the ferrule 13 opposing the crossplate 12 thus forms a first locking means ensuring the retention of the elastic means 11 in the compressed position.
  • control surfaces 2a to 2d are deployed and out of the body 5.
  • the shell 13 has turned a quarter turn in the direction 16 relative to the position it occupies on the figures 2 and 3 .
  • the spring 11 is released and pushes the thrust plate 12 against the racks 9.
  • Each arm of the plate 12 pushes a rack 9.
  • the racks 9a to 9d have been thrust of the plate 12 which causes them to penetrate deeper into each of the supports 8 control surfaces. In their final depressed position, the racks 9a to 9d penetrate deeper into the supports 8 of control surfaces passing right through them.
  • each of the racks 9a to 9d can independently follow the movements of control rudders controlled via the motors (not shown).
  • figure 6 which represents in detail a partial section along the orthogonal planes C identified at figure 3 of the device 4 in the configuration of the control surfaces 2a to 2d folded.
  • the shell 13 separates the thrust plate 12 from the rack 9a.
  • the rack 9a has on each of its lateral faces (symmetrical with respect to the teeth of the rack) a longitudinal groove 99a.
  • the rack thus has two grooves 99a.
  • One of these grooves 99a will be better seen at figure 7 where it can be seen that the grooves 99a only open at one end of the rack 9 and that they are used for the translational guiding of the rack 9a in the support 8, which comprises two tabs 88 engaged in the grooves 99a (one of the tabs 88 will be better seen on the figure 6 ).
  • the ferrule 13 comprises at the lug 13a a locking pin 16a which is placed on the face directed towards the rack 9a (the configuration of the shell 13 alone is better represented on the figure 8 which gives a glimpse of this one of the side oriented towards the racks 9).
  • the finger 16a is engaged in a single groove 99a of the rack 9a, at the end of the rack 9a where this groove 99a does not open. In this way the finger 16a locks the sliding of the rack 9a which also locks (via the pinion 6) the rudder 2a in the folded position in the body 5.
  • the cup of the figure 6 shows more particularly the rack 9a, but all the racks are structurally identical and the shell 13 also has identical locking fingers 16 disposed at each rack and engaged in a groove of the rack. Each locking pin 16a to 16d is secured to a lug 13a to 13d of the shell 13 (see FIG. figure 8 ).
  • each rack 9 comprises a housing 17 and each support 8 of rudder comprises a ball stop 18.
  • a housing 17 is formed on the rack 9 at a location such that when the rudder 2 is deployed, the stop ball 18 is engaged in the housing 17 thus forming a lock.
  • the stop thus immobilizes the rack 9 in translation with respect to its support 8, which also locks the rudder in the deployed position by means of the pinion 6.
  • the figure 9 shows in a partial manner another embodiment of the invention.
  • the thrust plate may, at the end of its axial displacement, partially pivot about the axis 28 on which it is mounted (axis coaxial with the axis of the projectile). This pivoting allows to separate each arm 12a to 12d of the thrust plate of the slider 9 that this arm has moved.
  • the axis 28 comprises a guide groove 28a which has a straight portion and which ends, at its end closest to the racks 9, by a helical portion.
  • this groove 28a circulates a tooth 30 integral with the thrust plate 12.
  • the helical pitch of the helical portion of the guide groove 28a will be chosen so as to rotate the thrust plate 12 by an angle such that at the end of the rotation each of the arms of the thrust plate 12 is no longer positioned in front of the slides 9.
  • the sliders 9 have been brought to the end of their stroke.
  • the angle of rotation ⁇ of the thrust plate 12 is of the order of one eighth of a revolution.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aerials With Secondary Devices (AREA)
  • Transmission Devices (AREA)

Description

Le domaine technique de l'invention est celui des dispositifs de déploiement des gouvernes de projectiles.The technical field of the invention is that of deployment devices projectile control surfaces.

Afin d'apporter une plus grande précision aux projectiles balistiques ou propulsés modernes, on équipe ceux ci de gouvernes pour corriger la trajectoire ou stabiliser le projectile. Ces gouvernes sont pilotées par des moteurs électriques. Compte tenu de l'encombrement représenté par les gouvernes, celles ci sont généralement contenues dans le corps du projectile pendant les phases de manutention et de mise en place dans un tube d'arme ainsi que durant la phase de balistique intérieure. Les gouvernes sont ensuite déployées en vol.In order to bring greater precision to modern ballistic or propelled projectiles, these are equipped with control surfaces to correct the trajectory or stabilize the projectile. These control surfaces are driven by electric motors. Given the congestion represented by the control surfaces, these are generally contained in the body of the projectile during the phases of handling and installation in a weapon tube and during the internal ballistic phase. The control surfaces are then deployed in flight.

Le brevet EP-1550837 propose pour déployer les gouvernes d'avoir recours à des ressorts équipant individuellement chacune des gouvernes. Ce dispositif présente un inconvénient majeur. Afin de ne pas compromettre la stabilité du projectile, il est primordial que le déploiement de toutes les gouvernes soit simultané, or ce dispositif n'apporte pas toutes les garanties nécessaires car il présente l'inconvénient que les ressorts ont des effets indépendants les uns des autres. De ce fait des différences d'élasticité ou d'autres caractéristiques mécaniques des ressorts risquent d'occasionner une sortie différée des gouvernes les unes par rapports aux autres.The patent EP-1550837 proposes to deploy the control surfaces to resort to springs equipping each control surfaces individually. This device has a major disadvantage. In order not to compromise the stability of the projectile, it is essential that the deployment of all control surfaces is simultaneous, but this device does not provide all the necessary guarantees because it has the disadvantage that the springs have effects independent of each other. other. As a result of the differences in elasticity or other mechanical characteristics of the springs may cause a deferred exit of the control surfaces relative to each other.

Il est décrit dans le brevet FR-1328459 un dispositif de déploiement simultané d'empennage à ailettes pour roquette. Le déploiement des ailettes fait appel à des secteurs dentés solidaires des ailettes qui engrènent avec une bague-crémaillère. Une seule et unique bague-crémaillère assure le déploiement simultané des ailettes.It is described in the patent FR-1328459 a device for simultaneous deployment of wing tail fin for rocket. The deployment of the fins uses toothed sectors fixed fins that meshing with a rack ring. A single rack and pinion ensures the simultaneous deployment of the fins.

De manière assez proche, DE-3838735 décrit un dispositif de déploiement simultané d'ailettes. Tout comme FR-1328459 , ce dispositif requiert un unique élément coulissant comportant une denture sur sa périphérie et engrenant avec les pignons de la base des ailettes.In a close way, DE-3838735 describes a device for simultaneous deployment of fins. As FR-1328459 , this device requires a single sliding element having a toothing on its periphery and meshing with the gears of the base of the fins.

L'inconvénient de ces solutions connues est que la bague dentée interdit tout pivotement de l'ailette après son déploiement. Ces solutions sont donc inadaptées pour déployer des gouvernes destinées à être pivotées par un moteur après leur déploiement pour assurer un pilotage du projectile.The disadvantage of these known solutions is that the toothed ring prevents any pivoting of the fin after deployment. These solutions are therefore inappropriate to deploy control surfaces intended to be pivoted by an engine after their deployment to ensure control of the projectile.

On connaît par ailleurs le brevet US-6880780 qui forme un point de départ pour la revendication 1 et qui décrit un dispositif de déploiement de gouvernes par le biais de bras de levier faisant également office de moyens de verrouillage des gouvernes en position repliées. Un tel dispositif est cependant particulièrement encombrant axialement et difficile à intégrer dans un projectile. Il est réservé aux projectiles de dimensions importantes tels que les missiles.The patent is also known US 6880780 which forms a starting point for claim 1 and which describes a device for deploying control surfaces by means of lever arms also acting as locking means of the control surfaces in the folded position. Such a device is however particularly bulky axially and difficult to integrate into a projectile. It is reserved for large projectiles such as missiles.

L'invention se propose de fournir une solution assurant un déploiement simultané de toutes les gouvernes. Pour cela l'énergie de déploiement est fournie par un unique ressort qui fait coulisser simultanément des crémaillères permettant le déploiement simultané des gouvernes tout en leur permettant une fois déployées de pouvoir pivoter sur elles-mêmes, par la commande d'un moteur, pour assurer le pilotage du projectile.The invention proposes to provide a solution ensuring simultaneous deployment of all the control surfaces. For this, the deployment energy is provided by a single spring which simultaneously slides racks allowing the simultaneous deployment of the control surfaces while allowing them once deployed to be pivoted on themselves, by the control of an engine, to ensure the steering of the projectile.

L'invention a pour objet un dispositif de déploiement de gouvernes d'un projectile pour lequel chaque gouverne est destinée à être pivotée par un moteur après déploiement pour assurer un pilotage, chaque gouverne étant maintenue à l'intérieur du projectile et déployée vers l'extérieur du projectile par la détente d'un moyen élastique, chaque gouverne se déployant par rotation par rapport à un support de gouverne et suivant un axe de déploiement transversal à l'axe du projectile. Ce dispositif de déploiement de gouvernes est caractérisé en ce que, le moyen élastique est un moyen commun qui assure le déploiement de l'ensemble des gouvernes, la détente du moyen élastique générant un effort de poussée dirigé suivant l'axe du projectile et s'exerçant sur une plaque de poussée qui transmet l'effort de poussée à autant de coulisseaux qu'il y a de gouvernes à déployer, chaque coulisseau coopérant sans glissement avec un profil complémentaire solidaire d'une base de la gouverne pour faire pivoter celle ci par rapport à son support et un premier moyen de verrouillage libérable assurant par ailleurs le maintien du moyen élastique en position comprimée.The invention relates to a device for deploying control surfaces of a projectile for which each rudder is intended to be pivoted by a motor after deployment to provide steering, each rudder being held inside the projectile and deployed to the outside the projectile by the expansion of an elastic means, each rudder unfolding by rotation relative to a steering support and a transverse axis of deployment to the axis of the projectile. This device for deploying control surfaces is characterized in that the elastic means is a common means which ensures the deployment of all the control surfaces, the expansion of the elastic means generating a thrust force directed along the axis of the projectile and exerting on a thrust plate which transmits the thrust force to as many sliders as there are control surfaces to be deployed, each slide cooperating without sliding with a complementary profile integral with a base of the rudder to rotate it by relative to its support and a first releasable locking means also ensuring the retention of the elastic means in the compressed position.

Selon un premier mode de réalisation, le premier moyen de verrouillage est constitué par une virole sensiblement cylindrique qui sépare la plaque de poussée des coulisseaux quand le moyen élastique est comprimé, la virole comportant des ergots sur lesquels viennent en butée des bras radiaux portés par la plaque de poussée, la virole pouvant pivoter suivant l'axe du projectile pour libérer la plaque de poussée et provoquer la détente du moyen élastique, les bras radiaux venant alors pousser les coulisseaux.According to a first embodiment, the first locking means is constituted by a substantially cylindrical ferrule which separates the thrust plate from the sliders when the resilient means is compressed, the ferrule comprising pins on which abutment radial arms carried by the thrust plate, the ferrule being pivotable along the axis of the projectile to release the thrust plate and cause the relaxation of the elastic means, the radial arms then pushing the slides.

Selon une autre caractéristique, le dispositif comporte un second moyen de verrouillage libérable qui maintient les gouvernes en position repliée.According to another characteristic, the device comprises a second releasable locking means which keeps the control surfaces in the folded position.

Selon encore une autre caractéristique, le dispositif comporte un troisième moyen de verrouillage maintenant les gouvernes en position déployée.According to yet another feature, the device comprises a third locking means maintaining the control surfaces in the deployed position.

Selon encore une autre caractéristique, la virole comporte une denture interne coopérant avec un second pignon entraîné par un moteur pour permettre le pivotement de la virole et le déverrouillage du moyen élastique.According to yet another characteristic, the ferrule comprises an internal toothing cooperating with a second pinion driven by a motor to allow the pivoting of the ferrule and the unlocking of the elastic means.

Selon encore une autre caractéristique, le second moyen de verrouillage comprend des doigts solidaires de la virole, chaque doigt s'engageant dans une rainure longitudinale du coulisseau, les doigts se dégageant de leurs rainures lors du pivotement de la virole.According to yet another feature, the second locking means comprises fingers integral with the ferrule, each finger engaging in a longitudinal groove of the slide, the fingers being disengaged from their grooves during the pivoting of the ferrule.

Selon encore une autre caractéristique, le troisième moyen de verrouillage est constitué pour chaque gouverne par au moins une butée à bille s'engageant dans un évidement du coulisseau quand les gouvernes sont déployées.According to yet another feature, the third locking means is constituted for each rudder by at least one ball stop engaging in a recess of the slide when the control surfaces are deployed.

Selon encore une autre caractéristique, le coulisseau est une crémaillère qui coopère avec un profil complémentaire formé par un premier pignon denté solidaire de la base de la gouverne.According to yet another characteristic, the slide is a rack which cooperates with a complementary profile formed by a first toothed gear integral with the base of the rudder.

Selon un autre mode de réalisation, la plaque de poussée, qui est montée coulissante sur un axe coaxial au projectile, pourra comporter une dent qui assurera son guidage sur cet axe, dent qui circule dans une rainure longitudinale qui se termine par une portion hélicoïdale, la plaque de poussée pivotant ainsi partiellement autour de l'axe à l'issue de son déplacement axial de façon à ce que chaque bras soit écarté du coulisseau qu'il a poussé.According to another embodiment, the thrust plate, which is slidably mounted on an axis coaxial with the projectile, may comprise a tooth which will ensure its guidance on this axis, a tooth which circulates in a longitudinal groove which ends with a helicoidal portion, the thrust plate pivoting thus partially around the axis at the end of its axial displacement so that each arm is moved away from the slide it pushed.

L'invention sera mieux comprise à la lecture de la description qui suit, description faisant référence aux dessins annexés et dans lesquels:

  • la figure 1 représente une vue d'ensemble du dispositif monté sur un projectile avec les gouvernes déployées,
  • la figure 2 représente une vue de trois quarts du dispositif avec les gouvernes repliées,
  • la figure 3 représente une vue en coupe longitudinale suivant un plan de coupe A, positionné à la figure 2, avec les gouvernes en positions repliées,
  • la figure 4 représente une vue de trois quarts du dispositif avec les gouvernes déployées,
  • la figure 5 représente une vue en coupe longitudinale suivant un plan de coupe B, positionné à la figure 4, avec les gouvernes en positions déployées,
  • la figure 6 représente une vue de détail suivant une coupe partielle C à plans orthogonaux positionnés à la figure 3, du moyen de verrouillage du dispositif en position gouvernes repliées,
  • la figure 7 représente une vue partielle des éléments du dispositif en position déployée,
  • la figure 8 représente une vue de trois quarts de la virole seule, et
  • la figure 9 représente une vue en écorché de trois quarts avant d'un autre mode de réalisation du dispositif.
The invention will be better understood on reading the description which follows, a description referring to the appended drawings and in which:
  • the figure 1 represents an overview of the device mounted on a projectile with the control surfaces deployed,
  • the figure 2 represents a three-quarter view of the device with the folded control surfaces,
  • the figure 3 represents a longitudinal sectional view along a sectional plane A, positioned at the figure 2 , with the control surfaces in folded positions,
  • the figure 4 represents a three-quarter view of the device with the control surfaces deployed,
  • the figure 5 represents a longitudinal sectional view along a sectional plane B, positioned at the figure 4 , with the control surfaces in deployed positions,
  • the figure 6 represents a detail view in a partial section C with orthogonal planes positioned at the figure 3 , locking means of the device in the folded control position,
  • the figure 7 represents a partial view of the elements of the device in the deployed position,
  • the figure 8 represents a three-quarter view of the ferrule alone, and
  • the figure 9 represents a cutaway view of three quarters before another embodiment of the device.

Selon la figure 1, un projectile 1 est équipé de gouvernes 2a, 2b, 2c et 2d représentées déployées et disposées au niveau d'une partie avant du projectile 1. En arrière et dans l'alignement du plan des gouvernes 2a à 2d se trouvent sur le projectile des fentes 3 dont seules deux sont représentées.According to figure 1 , a projectile 1 is equipped with rudders 2a, 2b, 2c and 2d shown deployed and arranged at a front part of the projectile 1. In the rear and in the alignment of the plane of the control surfaces 2a to 2d are located on the projectile slots 3 of which only two are represented.

Le dispositif de déploiement des gouvernes 4 est contenu dans la partie avant du projectile 1 et n'est donc pas visible sur le dessin dans son intégralité. En position repliée, les gouvernes 2a à 2d sont insérées dans les fentes 3 (configuration non représentée sur la figure).The deployment device of the control surfaces 4 is contained in the front part of the projectile 1 and is therefore not visible in the drawing in its entirety. In the folded position, the control surfaces 2a to 2d are inserted into the slots 3 (configuration not shown in the figure).

Selon la figure 2, le dispositif de déploiement comporte un corps 5 qui abrite les gouvernes 2a à 2d en position repliée (deux gouvernes seulement sont visibles sur la figure 2). La base de chaque gouverne 2a à 2d comporte une denture formant un pignon 6. Cette base formant pignon 6 est traversée par un axe 7 solidaire d'un support 8.According to figure 2 , the deployment device comprises a body 5 which houses the control surfaces 2a to 2d in the folded position (only two control surfaces are visible on the figure 2 ). The base of each rudder 2a to 2d comprises a toothing forming a pinion 6. This pinion base 6 is traversed by an axis 7 integral with a support 8.

Après le déploiement des gouvernes 2a à 2d, chaque support 8 est destiné à être pivoté suivant un axe perpendiculaire à l'axe du projectile pour permettre le pilotage. Ce pivotement est assuré par un moteur (non représenté). Le pignon 6 engrène avec un coulisseau denté (aussi nommé crémaillère 9) qui coulisse dans une rainure du corps 5.After the deployment of the control surfaces 2a to 2d, each support 8 is intended to be pivoted along an axis perpendicular to the axis of the projectile to enable control. This pivoting is provided by a motor (not shown). The pinion 6 meshes with a toothed slider (also called rack 9) which slides in a groove of the body 5.

Le dispositif de déploiement 4 comporte dans sa partie la plus en avant un capot 10 (seul un secteur du capot 10 est représenté) solidaire du corps 5. Ce capot 10 comporte en son centre un logement accueillant l'extrémité d'un moyen élastique comprimé qui est ici un ressort 11 à spires hélicoïdales. Une première extrémité du ressort 11 est en appui sur une plaque de poussée en forme de croix 12 qui comporte des bras radiaux (autant de bras radiaux qu'il y a de crémaillères 9).The deployment device 4 comprises in its foremost part a cover 10 (only one sector of the cover 10 is shown) integral with the body 5. This cover 10 comprises in its center a housing accommodating the end of a compressed elastic means which is here a spring 11 with helical turns. A first end of the spring 11 is supported on a cross-shaped thrust plate 12 which has radial arms (as many radial arms as there are racks 9).

Les bras de la plaque de poussée sont en appui chacun sur un ergot 13a à 13d solidaire d'une virole 13 (l'ergot 13c n'est pas visible sur la figure 2 car masqué par la portion de capot 10). La virole 13 est plus particulièrement visible sur la figure 8. Elle est sensiblement cylindrique et comporte une couronne à denture intérieure 14 sur son pourtour interne. Cette couronne dentée 14 engrène avec un pignon 15 entraîné par un moteur (non représenté). Les ergots 13a,13b,13c et 13d sont configurés sous la forme de languettes planes qui s'étendent radialement vers l'intérieur de la virole 13 et qui sont régulièrement réparties angulairement.The arms of the thrust plate are each supported on a lug 13a to 13d integral with a ferrule 13 (the lug 13c is not visible on the figure 2 because masked by the hood portion 10). The shell 13 is more particularly visible on the figure 8 . It is substantially cylindrical and has a ring gear with internal teeth 14 on its inner periphery. This ring gear 14 meshes with a pinion 15 driven by a motor (not shown). The lugs 13a, 13b, 13c and 13d are configured in the form of flat tabs which extend radially inwardly of the shell 13 and which are regularly distributed angularly.

Dans la configuration de la figure 2, les gouvernes 2a à 2d sont repliées et les ergots 13a à 13d de la virole 13 séparent les crémaillères 9 des bras de la plaque de poussée 12. De cette manière les crémaillères 9 ne subissent pas l'effort généré par le ressort 11 évitant ainsi le déploiement des gouvernes 2a à 2d. La virole 13 s'opposant à la plaque de poussée en croix 12 forme ainsi un premier moyen de verrouillage assurant le maintien du moyen élastique 11 en position comprimée.In the configuration of the figure 2 , the control surfaces 2a to 2d are folded and the lugs 13a to 13d of the shell 13 separate the racks 9 from the arms of the thrust plate 12. In this way the racks 9 do not undergo the force generated by the spring 11 thus avoiding the deployment of the control surfaces 2a to 2d. The ferrule 13 opposing the crossplate 12 thus forms a first locking means ensuring the retention of the elastic means 11 in the compressed position.

Selon la figure 3, on retrouve en coupe longitudinale le dispositif 4 avec les gouvernes 2a et 2c repliées. On distingue particulièrement les ergots 13a et 13c de la virole 13 qui séparent les crémaillères 9a et 9c des bras 12a et 12c de la plaque de poussée 12. On notera la position du ressort 11 qui est coaxiale au dispositif de déploiement 4 et enfilé sur un axe 28 solidaire du corps 5. La seconde extrémité du ressort prend appui sur la plaque de poussée 12 au fond d'un logement 12e centré sur l'axe 28.According to figure 3 , in longitudinal section, the device 4 with the control surfaces 2a and 2c folded. Particularly, the lugs 13a and 13c of the shell 13 which separate the racks 9a and 9c from the arms 12a and 12c of the thrust plate 12 are distinguished. Note the position of the spring 11 which is coaxial with the deployment device 4 and threaded on a axle 28 integral with the body 5. The second end of the spring bears on the thrust plate 12 at the bottom of a housing 12e centered on the axis 28.

Selon la figure 4, les gouvernes 2a à 2d sont déployées et sorties hors du corps 5. La virole 13 a tourné d'un quart de tour dans le sens 16 par rapport à la position qu'elle occupe sur les figures 2 et 3. Le ressort 11 est libéré et il pousse la plaque de poussée 12 contre les crémaillères 9. Chaque bras de la plaque 12 pousse une crémaillère 9.According to figure 4 , the control surfaces 2a to 2d are deployed and out of the body 5. The shell 13 has turned a quarter turn in the direction 16 relative to the position it occupies on the figures 2 and 3 . The spring 11 is released and pushes the thrust plate 12 against the racks 9. Each arm of the plate 12 pushes a rack 9.

Pour arriver à ce déploiement des gouvernes depuis l'état représenté aux figures 2 et 3, il y a eu rotation du pignon 15 (rotation provoquée par un moteur non représenté) de manière à faire tourner d'un quart de tour la virole 13 via la couronne à denture intérieure 14. Dès la rotation opérée, les ergots 13a à 13d ne retiennent plus la plaque de poussée en croix 12 qui joue alors son rôle en transmettant l'effort du ressort 11 aux crémaillères 9 (non visibles sur cette figure 4). Dès lors, les crémaillères 9 entraînent en rotation les gouvernes 2a à 2d autour des axes 7 via les pignons 6.To arrive at this deployment of the control surfaces since the state represented figures 2 and 3 , there has been rotation of the pinion 15 (rotation caused by a motor not shown) so as to rotate a quarter turn of the shell 13 via the ring gear 14. As soon as the rotation is carried out, the lugs 13a to 13d no longer retain the cross push plate 12 which then plays its role in transmitting the force of the spring 11 to the racks 9 (not visible on this figure 4 ). Therefore, the racks 9 rotate the control surfaces 2a to 2d around the axes 7 via the pinions 6.

Selon la figure 5, on retrouve en coupe longitudinale le dispositif 4 et les éléments tels que cités précédemment à l'exception du pignon 15 et de la couronne à denture intérieure 14 qui sont masquées par la plaque de poussée en croix 12. On notera le changement de position des gouvernes 2a à 2d qui sont déployées, la position des crémaillères 9a à 9d, de la plaque de poussée 12 et surtout le contact qui s'opère entre la plaque de poussée 12 et la surface correspondante de chaque crémaillère 9.According to figure 5 , in longitudinal section, the device 4 and the elements as mentioned above with the exception of the pinion 15 and the ring gear 14 which are masked by the crossplate 12. Note the change of position of the control surfaces 2a to 2d which are deployed, the position of the racks 9a to 9d, the thrust plate 12 and especially the contact which occurs between the thrust plate 12 and the corresponding surface of each rack 9.

Les crémaillères 9a à 9d ont subi une poussée de la plaque 12 qui les amène à pénétrer plus profondément dans chacun des supports 8 de gouvernes. Dans leur position enfoncée finale, les crémaillères 9a à 9d pénètrent plus profondément dans les supports 8 de gouvernes en les traversant de part en part.The racks 9a to 9d have been thrust of the plate 12 which causes them to penetrate deeper into each of the supports 8 control surfaces. In their final depressed position, the racks 9a to 9d penetrate deeper into the supports 8 of control surfaces passing right through them.

Au terme de leur mouvement de translation les crémaillères 9a à 9d ne sont plus en contact avec la plaque 12 (écart entre plaque et crémaillères non visible sur le dessin). De cette manière, chacune des crémaillères 9a à 9d peut suivre de manière indépendante les mouvements des supports de gouvernes pilotés via les moteurs (non représentés).At the end of their translational movement the racks 9a to 9d are no longer in contact with the plate 12 (gap between plate and racks not visible in the drawing). In this way, each of the racks 9a to 9d can independently follow the movements of control rudders controlled via the motors (not shown).

Selon la figure 6, qui représente en détail une coupe partielle selon les plans orthogonaux C repérés à la figure 3 du dispositif 4 en configuration gouvernes 2a à 2d repliées. La virole 13 sépare la plaque de poussée 12 de la crémaillère 9a. La crémaillère 9a comporte sur chacune de ses faces latérales (symétriques par rapport à la denture de la crémaillère) une rainure longitudinale 99a.According to figure 6 , which represents in detail a partial section along the orthogonal planes C identified at figure 3 of the device 4 in the configuration of the control surfaces 2a to 2d folded. The shell 13 separates the thrust plate 12 from the rack 9a. The rack 9a has on each of its lateral faces (symmetrical with respect to the teeth of the rack) a longitudinal groove 99a.

La crémaillère comporte ainsi deux rainures 99a. Une de ces rainures 99a sera mieux vue à la figure 7 où l'on constate que les rainures 99a ne débouchent qu'au niveau d'une seule extrémité de la crémaillère 9 et qu'elles sont utilisées pour le guidage en translation de la crémaillère 9a dans le support 8, qui comporte pour cela deux languettes 88 engagées dans les rainures 99a (une des languettes 88 sera mieux vue sur la figure 6).The rack thus has two grooves 99a. One of these grooves 99a will be better seen at figure 7 where it can be seen that the grooves 99a only open at one end of the rack 9 and that they are used for the translational guiding of the rack 9a in the support 8, which comprises two tabs 88 engaged in the grooves 99a (one of the tabs 88 will be better seen on the figure 6 ).

En référence à la figure 6, la virole 13 comporte au niveau de l'ergot 13a un doigt de blocage 16a qui est placé sur la face dirigée vers la crémaillère 9a (la configuration de la virole 13 seule est mieux représentée sur la figure 8 qui donne un aperçu de celle ci du coté orienté vers les crémaillères 9).With reference to the figure 6 , the ferrule 13 comprises at the lug 13a a locking pin 16a which is placed on the face directed towards the rack 9a (the configuration of the shell 13 alone is better represented on the figure 8 which gives a glimpse of this one of the side oriented towards the racks 9).

Le doigt 16a est engagé dans une seule rainure 99a de la crémaillère 9a, à l'extrémité de la crémaillère 9a où cette rainure 99a n'est pas débouchant. De cette manière le doigt 16a verrouille le coulissement de la crémaillère 9a ce qui verrouille aussi (par le biais du pignon 6) la gouverne 2a en position repliée dans le corps 5.The finger 16a is engaged in a single groove 99a of the rack 9a, at the end of the rack 9a where this groove 99a does not open. In this way the finger 16a locks the sliding of the rack 9a which also locks (via the pinion 6) the rudder 2a in the folded position in the body 5.

La coupe de la figure 6 montre plus particulièrement la crémaillère 9a, mais toutes les crémaillères sont identiques structurellement et la virole 13 comporte aussi des doigts de verrouillage 16 identiques disposés au niveau de chaque crémaillère et engagés dans une rainure de la crémaillère considérée. Chaque doigt de verrouillage 16a à 16d est solidaire d'un ergot 13a à 13d de la virole 13 (voir la figure 8).The cup of the figure 6 shows more particularly the rack 9a, but all the racks are structurally identical and the shell 13 also has identical locking fingers 16 disposed at each rack and engaged in a groove of the rack. Each locking pin 16a to 16d is secured to a lug 13a to 13d of the shell 13 (see FIG. figure 8 ).

Selon la vue de détail de la figure 7 valable pour toutes les gouvernes, chaque crémaillère 9 comporte un logement 17 et chaque support 8 de gouverne comporte une butée à bille 18. Un logement 17 est pratiqué sur la crémaillère 9 à un endroit tel que lorsque la gouverne 2 est déployée, la butée à bille 18 vient s'engager dans le logement 17 formant ainsi un verrou. La butée immobilise ainsi la crémaillère 9 en translation par rapport à son support 8, ce qui verrouille également la gouverne en position déployée par le biais du pignon 6.According to the detail view of the figure 7 valid for all the control surfaces, each rack 9 comprises a housing 17 and each support 8 of rudder comprises a ball stop 18. A housing 17 is formed on the rack 9 at a location such that when the rudder 2 is deployed, the stop ball 18 is engaged in the housing 17 thus forming a lock. The stop thus immobilizes the rack 9 in translation with respect to its support 8, which also locks the rudder in the deployed position by means of the pinion 6.

La figure 9 montre de façon partielle un autre mode de réalisation de l'invention.The figure 9 shows in a partial manner another embodiment of the invention.

Ce mode diffère du précédent en ce que la plaque de poussée peut, à l'issue de son déplacement axial, pivoter partiellement autour de l'axe 28 sur lequel elle est montée (axe coaxial à l'axe du projectile). Ce pivotement permet d'écarter chaque bras 12a à 12d de la plaque de poussée du coulisseau 9 que ce bras a déplacé.This mode differs from the previous one in that the thrust plate may, at the end of its axial displacement, partially pivot about the axis 28 on which it is mounted (axis coaxial with the axis of the projectile). This pivoting allows to separate each arm 12a to 12d of the thrust plate of the slider 9 that this arm has moved.

Une telle disposition permet d'éviter toute interférence ou tout frottement excessif entre les crémaillères 9 et la plaque de poussée 12 lors du pivotement ultérieur des gouvernes 2a à 2d portant les crémaillères.Such an arrangement makes it possible to avoid any interference or excessive friction between the racks 9 and the thrust plate 12 during the subsequent pivoting of the control surfaces 2a to 2d carrying the racks.

Pour cela, l'axe 28 comporte une rainure de guidage 28a qui comporte une partie droite et qui se termine, à son extrémité la plus proche des crémaillères 9, par une portion hélicoïdale. Dans cette rainure 28a circule une dent 30 solidaire de la plaque de poussée 12. Le pas d'hélice de la partie hélicoïdale de la rainure de guidage 28a sera choisi de manière à faire pivoter la plaque de poussée 12 d'un angle tel qu'au terme de la rotation chacun des bras de la plaque de poussée 12 ne soit plus positionné devant les coulisseaux 9. Cependant, les coulisseaux 9 ont bien été amenés au terme de leur course.For this, the axis 28 comprises a guide groove 28a which has a straight portion and which ends, at its end closest to the racks 9, by a helical portion. In this groove 28a circulates a tooth 30 integral with the thrust plate 12. The helical pitch of the helical portion of the guide groove 28a will be chosen so as to rotate the thrust plate 12 by an angle such that at the end of the rotation each of the arms of the thrust plate 12 is no longer positioned in front of the slides 9. However, the sliders 9 have been brought to the end of their stroke.

Selon le mode de réalisation de la figure 9, l'angle de rotation α de la plaque de poussée 12 est de l'ordre d'un huitième de tour.According to the embodiment of the figure 9 , the angle of rotation α of the thrust plate 12 is of the order of one eighth of a revolution.

Claims (9)

  1. A deployment device for the control surfaces (4) of a projectile (1) for which each control surface (2a to 2d) is intended to be pivoted by a motor after its deployment to ensure the piloting, each control surface being held within the projectile (1) and deployed towards the exterior of the projectile (1) by the expansion of elastic means (11), each control surface (2a to 2d) being deployed by a rotation with respect to a control surface support (8) and following a deployment axis that is crosswise to that of the projectile, control surface deployment device (4) wherein the elastic means (11) are common means to ensure the deployment of all the control surfaces (2a to 2d), the expansion of the elastic means (11) generating a push stress directed along the projectile's axis and being exerted on a push plate (12) which transmits the push stress to as many slides (9) as there are control surfaces (2a to 2d) to be deployed, each slide (9) cooperating without slipping with a matching profile (6) integral with a base of the control surface (2a to 2d) to make this pivot with respect to its support (8) and first releasable locking means (13) that maintain the elastic means (11) in the compressed position.
  2. A simultaneous deployment device for the control surfaces (4) of a projectile (1) according to Claim 1, wherein the first locking means (13) are constituted by a substantially cylindrical ferrule (13) that separates the push plate (12) of the slides (9) when the elastic means (11) are being compressed, the ferrule incorporating lugs (13a to 13d) abutting radial arms (12a to 12d) carried by the push plate (12), since the ferrule (13) is able to pivot following the projectile's axis to release the push plate and cause the expansion of the elastic means (11), the radial arms (12a to 12d) thereafter push the slides (9).
  3. A simultaneous deployment device for the control surfaces (4) of a projectile (1) according to Claims 1 or 2, wherein it incorporates second releasable locking means (16) holding the control surfaces (2a to 2d) in their retracted position.
  4. A simultaneous deployment device for the control surfaces (4) of a projectile (1) according to one of Claims 1 to 3, wherein it incorporates third locking means (18) holding the control surfaces (2a to 2d) in their deployed position.
  5. A simultaneous deployment device for the control surfaces (4) of a projectile (1) according to Claim 2, wherein the ferrule (13) incorporates internal toothing (14) cooperating with a second pinion (15) driven by a motor to enable the ferrule (13) to pivot and unlock the elastic means (11).
  6. A simultaneous deployment device for the control surfaces of a projectile according to Claim 3, wherein the second locking means (16) comprise fingers (16a to 16d) integral with the ferrule (13), each finger (16a to 16d) engaging in a longitudinal groove (99a to 99d) of the slide (9), the fingers (16a to 16d) disengaging from their grooves (99a to 99d) when the ferrule (13) pivots.
  7. A simultaneous deployment device for the control surfaces (2a to 2d) of a projectile (1) according to Claim 4, wherein the third locking means (18) are constituted for each control surface (2a to 2d) by at least one ball push bearing (18) engaging in a recess (17) in the slide (9) when the control surfaces (2a to 2d) are deployed.
  8. A simultaneous deployment device for the control surfaces (4) of a projectile (1) according to Claims 1 to 2, wherein the slide (9) is a rack (8) that cooperates with a matching profile (6) formed by a first toothed pinion (6) integral with the base of the control surface (2).
  9. A simultaneous deployment device for the control surfaces (4) of a projectile (1) according to one of Claims 2 to 8, wherein the push plate (12), which is mounting sliding along an axis (28) coaxial to the projectile, incorporates a tooth (30) to ensure its guidance on this axis (28), such tooth (30) moving in a longitudinal groove ending in a helicoidal portion, the push plate thereby partially pivoting around the axis (28) at the end of its axial displacement such that each arm (12a to 12d) is moved away from the slide (9) it has pushed.
EP11290029A 2010-01-28 2011-01-19 Device for simultaneously deploying control surfaces of a projectile Active EP2354755B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL11290029T PL2354755T3 (en) 2010-01-28 2011-01-19 Device for simultaneously deploying control surfaces of a projectile

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1000344A FR2955653A1 (en) 2010-01-28 2010-01-28 DEVICE FOR SIMULTANEOUS DEPLOYMENT OF GOVERNMENTS OF A PROJECTILE

Publications (2)

Publication Number Publication Date
EP2354755A1 EP2354755A1 (en) 2011-08-10
EP2354755B1 true EP2354755B1 (en) 2012-11-07

Family

ID=42563191

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11290029A Active EP2354755B1 (en) 2010-01-28 2011-01-19 Device for simultaneously deploying control surfaces of a projectile

Country Status (5)

Country Link
US (1) US8592737B2 (en)
EP (1) EP2354755B1 (en)
ES (1) ES2398733T3 (en)
FR (1) FR2955653A1 (en)
PL (1) PL2354755T3 (en)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2707673B1 (en) * 2011-05-13 2018-11-07 Leigh Aerosystems Corporation Ground-projectile guidance system
FR2986319B1 (en) * 2012-01-27 2014-03-14 Tda Armements Sas PILOTAGE TRUNK FOR GUIDED MUNITION
FR2995074A1 (en) 2012-08-31 2014-03-07 Nexter Munitions PROJECTILE WITH ORIENTABLE GOVERNMENTS AND METHOD OF ORDERING THE GOVERNMENTS OF SUCH PROJECTILE
US9429402B2 (en) 2013-04-24 2016-08-30 Simmonds Precision Products, Inc. Multi-stage drive mechanisms
US20160187111A1 (en) * 2014-08-10 2016-06-30 Jahangir S Rastegar Methods and Devices For Guidance and Control of High-Spin Stabilized Rounds
US9702673B1 (en) * 2014-09-24 2017-07-11 The United States Of America As Represented By The Secretary Of The Army Projectile tail boom with self-locking fin
US11371814B2 (en) 2015-08-24 2022-06-28 Leigh Aerosystems Corporation Ground-projectile guidance system
FR3041744B1 (en) * 2015-09-29 2018-08-17 Nexter Munitions ARTILLERY PROJECTILE HAVING A PILOTED PHASE.
WO2017062563A1 (en) 2015-10-08 2017-04-13 Leigh Aerosystems Corporation Ground-projectile system
US11150062B1 (en) * 2016-06-23 2021-10-19 Orbital Research Inc. Control actuation system, devices and methods for missiles, munitions and projectiles
FR3054030B1 (en) * 2016-07-18 2018-08-24 Nexter Munitions PROJECTILE COMPRISING A DEVICE FOR DEPLOYING A VESSEL OR AILT
US10308347B2 (en) * 2016-10-26 2019-06-04 Simmonds Precision Products, Inc. Wing tip aileron actuation system
US10641590B2 (en) 2016-10-26 2020-05-05 Simmonds Precision Products, Inc. Wing deployment and lock mechanism
US11040772B2 (en) * 2017-09-11 2021-06-22 Defendtex Pty Ltd Unmanned aerial vehicle
EP3543640B1 (en) * 2018-03-21 2024-08-14 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
CN113091524B (en) * 2021-03-18 2022-08-30 中北大学 One-dimensional ballistic resistive patch continuous correction mechanism capable of being repeatedly unfolded and method
CN114370790B (en) * 2021-12-22 2024-02-06 山西中辐核仪器有限责任公司 Trajectory two-dimensional correction mechanism
US12044513B2 (en) * 2022-06-14 2024-07-23 Raytheon Company Passively jettisoned control surface restraint and cover for tactical flight vehicles

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB759679A (en) * 1949-04-29 1956-10-24 Vickers Armstrongs Aircraft Improvements in guided missiles
FR1328459A (en) * 1962-04-18 1963-05-31 Soc Tech De Rech Ind Droppable rocket
DE1533909B2 (en) 1967-06-28 1975-04-10 Demag Ag, 4100 Duisburg Metallurgical vessel, in particular tiltable and / or rotating steelworks converter
DE3328520C1 (en) * 1983-08-06 1985-03-07 Diehl GmbH & Co, 8500 Nürnberg Tailplane for missiles
DE3838735C2 (en) * 1988-11-15 1997-12-18 Diehl Gmbh & Co Folding wing, especially for one floor
US6224013B1 (en) * 1998-08-27 2001-05-01 Lockheed Martin Corporation Tail fin deployment device
SE519764C2 (en) * 2000-08-31 2003-04-08 Bofors Defence Ab Canardfenaggregat
GB2367598A (en) 2000-10-04 2002-04-10 Combined Engineering Concepts A drive transmission for a stern or outboard drive of a watercraft
US6880780B1 (en) * 2003-03-17 2005-04-19 General Dynamics Ordnance And Tactical Systems, Inc. Cover ejection and fin deployment system for a gun-launched projectile
FR2864612B1 (en) * 2003-12-24 2007-11-23 Giat Ind Sa DEVICE FOR DEPLOYING THE FINS OF A PROJECTILE
FR2864613B1 (en) 2003-12-31 2006-03-17 Giat Ind Sa DEVICE FOR DEPLOYING AND DRIVING GOVERNS OF A PROJECTILE
FR2891618B1 (en) * 2005-10-05 2010-06-11 Giat Ind Sa DEVICE FOR DRIVING PROJECTILE GOVERNMENTS.
US7851734B1 (en) * 2007-08-21 2010-12-14 Lockheed Martin Corporation Acceleration activated fin release mechanism

Also Published As

Publication number Publication date
PL2354755T3 (en) 2013-03-29
US8592737B2 (en) 2013-11-26
US20110180655A1 (en) 2011-07-28
ES2398733T3 (en) 2013-03-21
FR2955653A1 (en) 2011-07-29
EP2354755A1 (en) 2011-08-10

Similar Documents

Publication Publication Date Title
EP2354755B1 (en) Device for simultaneously deploying control surfaces of a projectile
EP1550837B1 (en) Device for the deployment and the control of the control vanes of a projectile
EP2259006B1 (en) Opening and locking system for an empennage of a munition
CA3042195A1 (en) Locking device with rotary lock with flick-shift control
EP1045221B1 (en) Aerodynamic brake for reducing the velocity of a projectile on its trajectory
EP1953494B1 (en) Device for controlling ammunition with deployable control surfaces
CA2870996A1 (en) Actuating device for moving a thrust reverser
EP3485224B1 (en) Projectile comprising a device for deploying a wing or fin
EP1006335A1 (en) Device for reducing the velocity of a projectile on its trajectory
EP0105001B1 (en) Safety device with a rotatable housing for a spinning projectile
EP1524488B1 (en) Device for deploying a projectile fin
FR2846080A1 (en) Deployment and actuating system for projectile control surfaces mounted in pairs on transverse shafts rotated by motors and held in deployed position by locks
EP0021870B1 (en) Device for coupling and uncoupling missiles to or from other missiles or carrier aircraft
FR3035493A1 (en) BALLISTIC PROJECTILE COMPRISING A WING OPENING MECHANISM AND METHOD OF USING SUCH A BALLISTIC PROJECTILE
FR2846079A1 (en) Guided projectile control surface locking/unlocking and actuating system has lock fixed to control shaft rotated by motor
FR2796251A1 (en) MODULAR HELMET WITH SIMPLIFIED MOUNTING AND RESISTANT TO AERODYNAMIC CONSTRAINTS
EP3660441B1 (en) Device for deploying a deployable element, in particular a handle, for a weapon system
EP0016701A1 (en) Safety device for a pyrotechnic chain
EP2913628B1 (en) Artillery projectile warhead fuse comprising a braking device acting in flight direction
EP3524082B1 (en) Piece of jewellery with animation
EP3692324B1 (en) Fin blocking device and projectile having such a device
CH716238B1 (en) Animation piece for the field of jewelry or jewelry.
FR2893547A1 (en) Fuel tank flap for motor vehicle, has shutter with assembly having axle engaged in drum, and compression spring supported against ring and bottom wall, so that shutter is integrated with bowl and displaced towards its closing position
FR2797946A1 (en) Fin mounting for tube launched missile munition has rotary support mounted in fuselage to carry fin via secondary pivot
CH713578A2 (en) Pusher winding device for mechanical watch.

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20120210

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F42B 10/64 20060101ALI20120427BHEP

Ipc: F42B 10/14 20060101AFI20120427BHEP

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 583182

Country of ref document: AT

Kind code of ref document: T

Effective date: 20121115

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602011000417

Country of ref document: DE

Effective date: 20130103

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 583182

Country of ref document: AT

Kind code of ref document: T

Effective date: 20121107

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2398733

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20130321

REG Reference to a national code

Ref country code: NO

Ref legal event code: T2

Effective date: 20121107

REG Reference to a national code

Ref country code: PL

Ref legal event code: T3

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20121107

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130307

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

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

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130307

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130208

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

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

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

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130207

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

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

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130131

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

26N No opposition filed

Effective date: 20130808

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602011000417

Country of ref document: DE

Effective date: 20130808

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

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130119

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

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

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

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

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

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

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

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

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121107

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20110119

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130119

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

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

Ref country code: GB

Payment date: 20231219

Year of fee payment: 14

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

Ref country code: SE

Payment date: 20231219

Year of fee payment: 14

Ref country code: NO

Payment date: 20231221

Year of fee payment: 14

Ref country code: FR

Payment date: 20231219

Year of fee payment: 14

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

Ref country code: PL

Payment date: 20231221

Year of fee payment: 14

Ref country code: BE

Payment date: 20231219

Year of fee payment: 14

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

Ref country code: ES

Payment date: 20240202

Year of fee payment: 14

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

Ref country code: DE

Payment date: 20231219

Year of fee payment: 14

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

Ref country code: IT

Payment date: 20240102

Year of fee payment: 14