EP0690284A1 - Deploying device for a projectile wing - Google Patents

Deploying device for a projectile wing Download PDF

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Publication number
EP0690284A1
EP0690284A1 EP95401557A EP95401557A EP0690284A1 EP 0690284 A1 EP0690284 A1 EP 0690284A1 EP 95401557 A EP95401557 A EP 95401557A EP 95401557 A EP95401557 A EP 95401557A EP 0690284 A1 EP0690284 A1 EP 0690284A1
Authority
EP
European Patent Office
Prior art keywords
fin
projectile
drive
lateral
fins
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.)
Granted
Application number
EP95401557A
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German (de)
French (fr)
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EP0690284B1 (en
Inventor
Bruno Lang
Michel Schillin
Jean-Gabriel Misse
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.)
Luchaire Defense SA
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Luchaire Defense SA
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Publication date
Application filed by Luchaire Defense SA filed Critical Luchaire Defense SA
Publication of EP0690284A1 publication Critical patent/EP0690284A1/en
Application granted granted Critical
Publication of EP0690284B1 publication Critical patent/EP0690284B1/en
Anticipated expiration legal-status Critical
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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 present invention relates to a device for deploying a stabilizing wing of a projectile, in particular a projectile fired by a recoilless weapon.
  • Certain projectiles in particular those fired by a smooth tube such as that of a recoilless weapon, have stabilization fins at their rear part. These fins are folded back when the projectile is in the launch tube and they deploy at the exit of this one.
  • Known deployment devices most often use springs which are kept in a tension state when the fins are folded along the body of the projectile and which relax by deploying the fin at the outlet of the launch tube.
  • Patent FR7803397 describes such a deployment device.
  • the subject of the invention is a device for deploying a stabilization fin for a projectile which is characterized in that it comprises at least one pallet, made integral with a fin by means drive, and oriented so as to receive an aerodynamic flow during the firing of the projectile and thus to transmit a resultant force to the fin in order to deploy it.
  • Another advantage of this arrangement is that it allows maximum force to be exerted at the start of the opening, when the resistant forces are also the greatest.
  • the drive means of the fin are unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.
  • the device comprises at least two pallets separated by a groove in which the fin is positioned, the groove having a bottom on which the fin comes to bear when it is in the folded position along the projectile body and which constitutes the drive means.
  • the device comprises a front wall closing the groove at a front part of the device and which constitutes an axial stop for the end of the fin.
  • the device comprises at least two lateral support feet which are in contact with an external surface of the projectile and which are held by abutment profiles carried by the projectile and arranged so as to prevent any displacement of the device in a direction perpendicular to a lateral surface of the fin.
  • the device comprises at least one pallet integral with at least two lateral drive surfaces, each of these surfaces drive being intended to receive the support of a fin different from the projectile when the latter are in the folded position along the projectile body.
  • the device comprises a tongue intended to come into abutment against a flange secured to the projectile and which constitutes an axial stop for the device.
  • the device comprises at least one wall substantially perpendicular to each drive surface and constituting an axial stop for the end of the fin considered.
  • each lateral drive surface includes a zone for holding a first lateral surface of the fin.
  • the device comprises an external guide surface with a circular profile and whose diameter is equal to that of a projectile launching tube.
  • FIG. 1 schematically represents the rear part of a projectile 1 intended to be fired by a recoilless launcher of known type (not shown).
  • This rear part comprises a flange 2 on which are fitted screeds 3 regularly angularly distributed.
  • Each yoke receives a fin 4, pivotally mounted around an axis 5.
  • the projectile thus represented therefore carries six fins 4 regularly distributed (see FIG. 2).
  • the fins 4 are shown here in their folded position along the body of the projectile 1, which is their position inside the launch tube.
  • Each fin 4 carries at a front end 4a a deployment device 6 according to the invention (here a single device is shown for clarity of the figure).
  • the device 6 comprises two paddles 7a and 7b for receiving the aerodynamic flow which appears during firing along the body la of the projectile between the front part (mark AV) and the rear part (mark AR).
  • These pallets have substantially the shape of two planes inclined with respect to the axis 8 of the projectile and perpendicular to the lateral surfaces 4b and 4c of the fin 4.
  • the inclination of the pallets relative to the axis 8 of the projectile is chosen such that the aerodynamic flow has the effect of moving the device 6 away from the body la of the projectile.
  • the device according to the invention can only be used to deploy fins which in the rest position are folded along the body of the projectile, the free ends of the fins being oriented towards the front part. of the projectile and the screeds being arranged at the rear thereof.
  • FIGS. 3a, 3b and 3c show in detail the deployment device 6.
  • This device is made for example from molded plastic (such as high density polyethylene or polyamide). The material thickness is substantially constant for the entire device.
  • Pallets 7a and 7b are connected to side walls 8a and 8b which end with lateral support legs 9a and 9b.
  • the side walls 8a, 8b are planar and substantially parallel to the side surfaces 4b, 4c of the fin 4.
  • the device after its installation on the projectile, is shaped so as to present opposite the aerodynamic flow two channels 6a, 6b whose inlet openings (arranged towards the front part AV of the projectile) have a surface greater than the outlet openings (oriented towards the rear rear part), this due to the inclination of the pallet.
  • the support feet 9a, 9b are intended to come into contact with the external surface of the body la of the projectile, they therefore have a cylindrical profile with a diameter equal to that of the body la of the projectile.
  • the two pallets 7a and 7b are separated by a groove 10 in which the fin 4 is positioned.
  • the groove 10 has a bottom 10a on which the fin comes to bear when it is in the folded position along the body 1a of the projectile.
  • the groove 10 is closed by a front wall 11 at the level of a front part of the device 6.
  • the end 4a of the fin is in axial abutment on the wall 11.
  • the fin balances the inertia forces to which the pallet is subjected when fired.
  • the width of the groove 10 will be chosen such that there is no play when the device 6 is placed on the fin.
  • the feet 9a and 9b of the device are held laterally by abutment profiles 12 carried by the projectile. These profiles 12 are arranged so as to prevent any movement of the device in a direction perpendicular to the lateral surfaces 4b, 4c of the fin 4.
  • the abutment profiles 12 could also play the role of axial abutment for the device, it would then suffice to provide a recess on each foot preventing any recoil of the device.
  • the deflection of the fin is avoided during its journey inside the launching tube, which avoids vibrations from the end of the fin at the exit of the tube and improves the deployment process and the stabilization of the projectile.
  • FIG. 2 represents in section along the plane AA of FIG. 1 the projectile 1 placed in a launching tube 13.
  • the device 6 has an external guide surface 14 whose diameter is equal to that of the launch tube 13. The device thus improves the guiding of the projectile in the launch tube.
  • the operation of the device is as follows.
  • the fins are firmly held by the device all along the path inside the launch tube.
  • the aerodynamic flow enters the openings 6a and 6b and exerts a force on the pallets 7a and 7b. This effort separates the devices 6 from the body 1a of the projectile, which has the effect of driving the fins 4 via the bottom 10a of the grooves 10 and of the partition 11.
  • All the fins are symmetrically open, mainly because, thanks to the device according to the invention, the force applied to the fin is of aerodynamic origin and it is maximum at the start of the opening. Symmetry is also favored by the absence of vibrations of the fin obtained thanks to the transverse setting provided by the stop profiles 12.
  • the device according to the invention therefore makes it possible to avoid the problems encountered with known deployment springs whose mechanical characteristics are liable to deteriorate during storage of the projectile.
  • the result of the aerodynamic forces as well as the centrifugal force which are exerted on the device 6 manage to overcome the friction between the fin and the groove 10 and cause the separation of the device and the 'fin.
  • the devices are automatically ejected and do not disturb the flight of the projectile by causing aerodynamic braking.
  • FIG. 4 thus shows by way of example a device in which the bottom 11 is set back relative to the inlet openings of the channels 6a, 6b.
  • FIG. 5 schematically represents the rear part of a projectile 1 equipped with a deployment device 15 according to a second embodiment of the invention which is intended for projectiles equipped with an even number of fins.
  • This device comprises a pallet 7 intended to receive the aerodynamic flow which appears during the firing along the body of the projectile between the front part (mark AV) and the rear part (mark AR).
  • the inclination of the pallet relative to the axis 8 of the projectile is also chosen such that the aerodynamic flow has the effect of separating the device 15 from the body 1a of the projectile.
  • FIGS 7a, 7b and 7c show in detail this deployment device.
  • the pallet 7 is connected to side walls 8a and 8b which terminate in lateral support legs 9a and 9b.
  • the side walls 8a, 8b are planar and substantially parallel to the side surfaces 4b, 4c of the fin 4.
  • the device after its installation on the projectile, is shaped so as to present, facing the aerodynamic flow, a channel 15a whose inlet opening (disposed towards the front part AV of the projectile) has a surface greater than that of the outlet opening (oriented towards the rear part AR).
  • the support feet 9a, 9b come into contact with the external surface of the body la of the projectile, they have a cylindrical profile with a diameter equal to that of this body.
  • Each surface 16a, 16b therefore receives a different fin when the latter are in the folded position along the body la of the projectile.
  • the feet 9a, 9b also carry holding zones 17a, 17b which are each in contact with a lateral surface of the fin considered.
  • three devices 15 according to the invention make it possible to deploy six fins.
  • Each fin is held laterally on one side by a holding zone 17 carried by one of the devices 15 and on the other by a stop profile 18 secured to a flange 19 also made of plastic and made integral with the body of projectile, for example by bonding.
  • the flanges are offset axially relative to the device, this so that the flanges do not prevent the opening of the fin.
  • the dimensions of the devices 15 and of the flanges 19 will be chosen so that there is no play when it is placed on the fin.
  • Such an arrangement makes it possible to immobilize the ends of the fins, which prevents vibrations during shooting and improves the deployment process and the stabilization of the projectile.
  • Each device 15 finally comprises a rear tongue 20 which is intended to come into abutment against a flange 21 of the projectile and which constitutes an axial stop for the device.
  • the tongue also makes it possible to locate, at the rear flange and at an equal distance from each fin, the pivot point of the device. Such an arrangement ensures symmetrical opening of the two fins by the device.
  • the device 15 has an external guide surface 14 whose diameter is equal to that of the launch tube 13. The device thus improves the guiding of the projectile in the launch tube.
  • the deployment device is still ejected from a certain angle of opening of the fins.
  • An advantage of this embodiment is that it makes it possible to eject the device very quickly, which reduces its action to a simple initial impulse on the fins which then terminate their opening by inertia and by the effect of their own drag.
  • the rapid ejection of the device also has the advantage of limiting the angular speed of the fin at the end of the stroke, which limits the rebounds of the fin and improves the stabilization of the projectile.
  • the distance between the ends of two neighboring fins increases during opening.
  • the fins are therefore quickly released from the drive surfaces 16a, 16b and it is possible to precisely determine the instant of ejection of the device by adjusting the dimensions of the drive surfaces 16a, 16b and in particular over the length L ( see Figures 6 and 7a).
  • Another advantage of this embodiment is that it makes it possible to reduce the number of devices used for a projectile, and therefore the cost of production.
  • a deployment device which would remain integral with the fin even after deployment.
  • Such a device would for example include one or more pallets fixed to the side walls of each fin.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Pallets (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Iron Core Of Rotating Electric Machines (AREA)

Abstract

The deployment system, e.g. for a missile fired from a recoil-less weapon, consists of a bracket (7a,7b) attached to each fin (4) and positioned so as to receive an aerodynamic flow on missile launch and transmit it to the fin to deploy it, separating from the fin once it reaches a certain angle. The bracket is in two sections with a slot (10) between for the fin. The slot is closed at its forward end by a cross-piece (11) between the bracket sections. Stops (12) on either side of the brackets prevent any lateral movement. <IMAGE>

Description

La présente invention a pour objet un dispositif de déploiement d'ailette de stabilisation d'un projectile, notamment d'un projectile tiré par une arme sans recul.The present invention relates to a device for deploying a stabilizing wing of a projectile, in particular a projectile fired by a recoilless weapon.

Certains projectiles, notamment ceux tirés par un tube lisse tel celui d'une arme sans recul, comportent des ailettes de stabilisation à leur partie arrière. Ces ailettes sont repliées lorsque le projectile se trouve dans le tube de lancement et elles se déploient à la sortie de celui ci.Certain projectiles, in particular those fired by a smooth tube such as that of a recoilless weapon, have stabilization fins at their rear part. These fins are folded back when the projectile is in the launch tube and they deploy at the exit of this one.

Les dispositifs de déploiement connus mettent le plus souvent en oeuvre des ressorts qui sont maintenus en état de tension lorsque les ailettes sont repliées le long du corps du projectile et qui se détendent en déployant l'ailette à la sortie du tube de lancement.Known deployment devices most often use springs which are kept in a tension state when the fins are folded along the body of the projectile and which relax by deploying the fin at the outlet of the launch tube.

Le brevet FR7803397 décrit un tel dispositif de déploiement.Patent FR7803397 describes such a deployment device.

L'inconvénient de tels dispositifs est qu'ils imposent le maintien à l'état bandé de plusieurs ressorts (un par ailette) pendant toute la durée de stockage du projectile.The disadvantage of such devices is that they require several springs (one per fin) to be kept in the bandaged state during the entire duration of storage of the projectile.

Les caractéristiques mécaniques des ressorts se dégradent au cours du temps et il en résulte, d'une part une diminution de l'efficacité du déploiement, et d'autre part des dissymétries lors de l'ouverture des ailettes, qui nuisent à la stabilisation du projectile sur trajectoire donc à la précision du tir.The mechanical characteristics of the springs deteriorate over time and this results, on the one hand, in a reduction in the efficiency of deployment, and on the other hand, asymmetries during the opening of the fins, which harm the stabilization of the projectile on trajectory therefore with the precision of the shooting.

De plus, la mise en place de ressorts impose la réalisation sur le corps de projectile de logements pour ceux-ci, et pose des problèmes lors du montage et du contrôle, ce qui augmente les coûts de fabrication.In addition, the installation of springs imposes the realization on the projectile body of housings for these, and poses problems during mounting and control, which increases the manufacturing costs.

C'est le but de l'invention que de proposer un dispositif de déploiement d'ailettes de stabilisation pour un projectile qui ne présente pas de tels inconvénients et qui assure à moindre coût un déploiement efficace et symétrique des ailettes de stabilisation.It is the object of the invention to propose a device for deploying stabilizing fins for a projectile which does not have such drawbacks and which ensures an efficient and symmetrical deployment of the stabilizing fins at a low cost.

Ainsi l'invention a pour objet un dispositif de déploiement d'ailette de stabilisation pour un projectile qui est caractérisé en ce qu'il comporte au moins une palette, rendue solidaire d'une ailette par des moyens d'entraînement, et orientée de façon à recevoir un écoulement aérodynamique lors du tir du projectile et à transmettre ainsi un effort résultant à l'ailette afin de la déployer.Thus, the subject of the invention is a device for deploying a stabilization fin for a projectile which is characterized in that it comprises at least one pallet, made integral with a fin by means drive, and oriented so as to receive an aerodynamic flow during the firing of the projectile and thus to transmit a resultant force to the fin in order to deploy it.

Une telle disposition permet d'éviter pour ouvrir l'ailette l'emploi d'une énergie potentielle élastique stockée dans des ressorts.Such an arrangement makes it possible to avoid, to open the fin, the use of a potential elastic energy stored in springs.

Un autre avantage de cette disposition est qu'elle permet d'exercer une force maximale au début de l'ouverture, lorsque les efforts résistants sont également les plus grands.Another advantage of this arrangement is that it allows maximum force to be exerted at the start of the opening, when the resistant forces are also the greatest.

Selon une autre caractéristique de l'invention, les moyens d'entraînement de l'ailette sont déverrouillables de façon à séparer le dispositif de déploiement et l'ailette à partir d'un certain angle d'ouverture de cette dernière.According to another characteristic of the invention, the drive means of the fin are unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter.

On évite ainsi toute traînée aérodynamique résiduelle occasionnée par le dispositif. En libérant l'ailette assez tôt on limite également les rebonds de cette dernière.This avoids any residual aerodynamic drag caused by the device. By releasing the fin early enough, the rebounds of the latter are also limited.

Selon un premier mode de réalisation, le dispositif comporte au moins deux palettes séparées par une rainure dans laquelle se positionne l'ailette, la rainure comportant un fond sur lequel l'ailette vient en appui lorsqu'elle se trouve en position repliée le long du corps de projectile et qui constitue le moyen d'entraînement.According to a first embodiment, the device comprises at least two pallets separated by a groove in which the fin is positioned, the groove having a bottom on which the fin comes to bear when it is in the folded position along the projectile body and which constitutes the drive means.

Selon une particularité de réalisation, le dispositif comporte une paroi frontale fermant la rainure au niveau d'une partie avant du dispositif et qui constitue une butée axiale pour l'extrémité de l'ailette.According to a particular embodiment, the device comprises a front wall closing the groove at a front part of the device and which constitutes an axial stop for the end of the fin.

Selon une autre particularité de réalisation, le dispositif comporte au moins deux pieds d'appui latéraux qui sont en contact avec une surface externe du projectile et qui sont maintenus par des profils de butée portés par le projectile et disposés de façon à empêcher tout déplacement du dispositif suivant une direction perpendiculaire à une surface latérale de l'ailette.According to another particular feature, the device comprises at least two lateral support feet which are in contact with an external surface of the projectile and which are held by abutment profiles carried by the projectile and arranged so as to prevent any displacement of the device in a direction perpendicular to a lateral surface of the fin.

Selon un deuxième mode de réalisation, le dispositif comporte au moins une palette solidaire d'au moins deux surfaces d'entraînement latérales, chacune de ces surfaces d'entraînement étant destinée à recevoir l'appui d'une ailette différente du projectile lorsque ces dernières se trouvent en position repliée le long du corps de projectile.According to a second embodiment, the device comprises at least one pallet integral with at least two lateral drive surfaces, each of these surfaces drive being intended to receive the support of a fin different from the projectile when the latter are in the folded position along the projectile body.

Selon une particularité de réalisation, le dispositif comporte une languette destinée à venir en appui contre une collerette solidaire du projectile et qui constitue une butée axiale pour le dispositif.According to a particular embodiment, the device comprises a tongue intended to come into abutment against a flange secured to the projectile and which constitutes an axial stop for the device.

Selon une variante, le dispositif comporte au moins une paroi sensiblement perpendiculaire à chaque surface d'entraînement et constituant une butée axiale pour l'extrémité de l'ailette considérée.According to a variant, the device comprises at least one wall substantially perpendicular to each drive surface and constituting an axial stop for the end of the fin considered.

Selon une autre particularité de réalisation, chaque surface d'entraînement latérale comporte une zone de maintien d'une première surface latérale de l'ailette.According to another particular feature, each lateral drive surface includes a zone for holding a first lateral surface of the fin.

Selon une autre caractéristique, le dispositif comporte une surface de guidage externe à profil circulaire et dont le diamètre est égal à celui d'un tube de lancement du projectile.According to another characteristic, the device comprises an external guide surface with a circular profile and whose diameter is equal to that of a projectile launching tube.

D'autres avantages de l'invention apparaîtront à la lecture de la description de différents modes de réalisation, description faite en référence aux dessins annexés et dans lesquels:

  • la figure 1 représente partiellement la partie arrière d'un projectile équipé d'un dispositif de déploiement d'ailettes selon un premier mode de réalisation de l'invention,
  • la figure 2 est une vue en coupe transversale de la partie arrière de ce projectile au niveau des dispositifs de déploiement d'ailettes, suivant le plan repéré AA sur la figure 1,
  • les figures 3a, 3b et 3c représentent ce premier dispositif de déploiement d'ailettes suivant trois vues orthogonales,
  • la figure 4 représente une variante de ce dispositif,
  • la figure 5 représente partiellement la partie arrière d'un projectile équipé d'un dispositif de déploiement d'ailettes selon un deuxième mode de réalisation de l'invention,
  • la figure 6 est une vue en coupe transversale de la partie arrière de ce projectile au niveau des dispositifs de déploiement d'ailettes, suivant le plan repéré BB sur la figure 5,
  • les figures 7a, 7b et 7c représentent ce deuxième dispositif de déploiement d'ailettes suivant trois vues orthogonales.
Other advantages of the invention will appear on reading the description of different embodiments, description made with reference to the appended drawings and in which:
  • FIG. 1 partially represents the rear part of a projectile equipped with a device for deploying fins according to a first embodiment of the invention,
  • FIG. 2 is a cross-sectional view of the rear part of this projectile at the level of the fins deployment devices, along the plane marked AA in FIG. 1,
  • FIGS. 3a, 3b and 3c represent this first device for deploying fins in three orthogonal views,
  • FIG. 4 represents a variant of this device,
  • FIG. 5 partially represents the rear part of a projectile equipped with a device for deploying fins according to a second embodiment of the invention,
  • FIG. 6 is a cross-sectional view of the rear part of this projectile at the level of the fins deployment devices, along the plane marked BB in FIG. 5,
  • Figures 7a, 7b and 7c show this second device for deploying fins in three orthogonal views.

La figure 1 représente schématiquement la partie arrière d'un projectile 1 destiné à être tiré par un lanceur sans recul de type connu (non représenté).FIG. 1 schematically represents the rear part of a projectile 1 intended to be fired by a recoilless launcher of known type (not shown).

Cette partie arrière comprend une collerette 2 sur laquelle sont aménagées des chapes 3 régulièrement réparties angulairement. Chaque chape reçoit une ailette 4, montée pivotante autour d'un axe 5.This rear part comprises a flange 2 on which are fitted screeds 3 regularly angularly distributed. Each yoke receives a fin 4, pivotally mounted around an axis 5.

Le projectile ainsi représenté porte donc six ailettes 4 régulièrement réparties (voir figure 2).The projectile thus represented therefore carries six fins 4 regularly distributed (see FIG. 2).

Les ailettes 4 sont représentées ici dans leur position repliée le long du corps la de projectile 1, position qui est la leur à l'intérieur du tube de lancement.The fins 4 are shown here in their folded position along the body of the projectile 1, which is their position inside the launch tube.

Chaque ailette 4 porte au niveau d'une extrémité avant 4a un dispositif de déploiement 6 selon l'invention (ici un seul dispositif est représenté pour la clarté de la figure).Each fin 4 carries at a front end 4a a deployment device 6 according to the invention (here a single device is shown for clarity of the figure).

Selon le premier mode de réalisation décrit, le dispositif 6 comporte deux palettes 7a et 7b de réception de l'écoulement aérodynamique qui apparait lors du tir le long du corps la du projectile entre la partie avant (repère AV) et la partie arrière (repère AR).According to the first embodiment described, the device 6 comprises two paddles 7a and 7b for receiving the aerodynamic flow which appears during firing along the body la of the projectile between the front part (mark AV) and the rear part (mark AR).

Ces palettes ont sensiblement la forme de deux plans inclinés par rapport à l'axe 8 du projectile et perpendiculaires aux surfaces latérales 4b et 4c de l'ailette 4.These pallets have substantially the shape of two planes inclined with respect to the axis 8 of the projectile and perpendicular to the lateral surfaces 4b and 4c of the fin 4.

L'inclinaison des palettes par rapport à l'axe 8 du projectile est choisie telle que l'écoulement aérodynamique ait pour effet d'écarter le dispositif 6 du corps la du projectile.The inclination of the pallets relative to the axis 8 of the projectile is chosen such that the aerodynamic flow has the effect of moving the device 6 away from the body la of the projectile.

Ainsi du fait du mode d'action utilisé, le dispositif selon l'invention ne peut être employé que pour déployer des ailettes qui en position de repos sont repliées le long du corps du projectile, les extrémités libres des ailettes étant orientées vers la partie avant du projectile et les chapes étant disposées à l'arrière de celui-ci.Thus, because of the mode of action used, the device according to the invention can only be used to deploy fins which in the rest position are folded along the body of the projectile, the free ends of the fins being oriented towards the front part. of the projectile and the screeds being arranged at the rear thereof.

Les figures 3a, 3b et 3c représentent en détail le dispositif de déploiement 6.FIGS. 3a, 3b and 3c show in detail the deployment device 6.

Ce dispositif est réalisé par exemple en matière plastique moulée (telle du polyéthylène haute densité ou du polyamide). L'épaisseur de matière est sensiblement constante pour tout le dispositif. Les palettes 7a et 7b sont reliées à des parois latérales 8a et 8b qui se terminent par des pieds d'appui latéraux 9a et 9b.This device is made for example from molded plastic (such as high density polyethylene or polyamide). The material thickness is substantially constant for the entire device. Pallets 7a and 7b are connected to side walls 8a and 8b which end with lateral support legs 9a and 9b.

Les parois latérales 8a, 8b sont planes et sensiblement parallèles aux surfaces latérales 4b,4c de l'ailette 4.The side walls 8a, 8b are planar and substantially parallel to the side surfaces 4b, 4c of the fin 4.

Le dispositif, après sa mise en place sur le projectile, se trouve conformé de façon à présenter en regard de l'écoulement aérodynamique deux canaux 6a,6b dont les ouvertures d'entrée (disposées vers la partie avant AV du projectile) ont une surface supérieure aux ouvertures de sortie (orientées vers la partie arrière AR), cela en raison de l'inclinaison de la palette.The device, after its installation on the projectile, is shaped so as to present opposite the aerodynamic flow two channels 6a, 6b whose inlet openings (arranged towards the front part AV of the projectile) have a surface greater than the outlet openings (oriented towards the rear rear part), this due to the inclination of the pallet.

Les pieds d'appui 9a,9b sont destinés à venir en contact avec la surface externe du corps la du projectile, ils ont donc un profil cylindrique de diamètre égal à celui du corps la du projectile.The support feet 9a, 9b are intended to come into contact with the external surface of the body la of the projectile, they therefore have a cylindrical profile with a diameter equal to that of the body la of the projectile.

Les deux palettes 7a et 7b sont séparées par une rainure 10 dans laquelle se positionne l'ailette 4.The two pallets 7a and 7b are separated by a groove 10 in which the fin 4 is positioned.

La rainure 10 comporte un fond 10a sur lequel l'ailette vient en appui lorsqu'elle se trouve en position repliée le long du corps 1a de projectile.The groove 10 has a bottom 10a on which the fin comes to bear when it is in the folded position along the body 1a of the projectile.

La rainure 10 est fermée par une paroi frontale 11 au niveau d'une partie avant du dispositif 6. Quand le dispositif 6 est mis en place sur le projectile, l'extrémité 4a de l'ailette est en butée axiale sur la paroi 11. Ainsi l'ailette équilibre les efforts d'inertie auxquels est soumise la palette lors du tir.The groove 10 is closed by a front wall 11 at the level of a front part of the device 6. When the device 6 is placed on the projectile, the end 4a of the fin is in axial abutment on the wall 11. Thus the fin balances the inertia forces to which the pallet is subjected when fired.

La largeur de la rainure 10 sera choisie telle qu'il n'y ait pas de jeu lors de la mise en place du dispositif 6 sur l'ailette.The width of the groove 10 will be chosen such that there is no play when the device 6 is placed on the fin.

De plus les pieds 9a et 9b du dispositif sont maintenus latéralement par des profils de butée 12 portés par le projectile. Ces profils 12 sont disposés de façon à empêcher tout déplacement du dispositif suivant une direction perpendiculaire aux surfaces latérales 4b,4c de l'ailette 4.In addition, the feet 9a and 9b of the device are held laterally by abutment profiles 12 carried by the projectile. These profiles 12 are arranged so as to prevent any movement of the device in a direction perpendicular to the lateral surfaces 4b, 4c of the fin 4.

A titre de variante les profils de butée 12 pourraient également jouer le rôle de butée axiale pour le dispositif, il suffirait alors de prévoir un décrochement sur chaque pied interdisant tout recul du dispositif.As a variant, the abutment profiles 12 could also play the role of axial abutment for the device, it would then suffice to provide a recess on each foot preventing any recoil of the device.

En immobilisant le dispositif, d'une part par rapport à l'ailette et d'autre part par rapport au corps de projectile, on évite la flexion de l'ailette pendant son parcours à l'intérieur du tube de lancement, ce qui évite les vibrations de l'extrémité de l'ailette à la sortie du tube et améliore le processus de déploiement et la stabilisation du projectile.By immobilizing the device, on the one hand with respect to the fin and on the other hand with respect to the projectile body, the deflection of the fin is avoided during its journey inside the launching tube, which avoids vibrations from the end of the fin at the exit of the tube and improves the deployment process and the stabilization of the projectile.

La figure 2 représente en coupe suivant le plan AA de la figure 1 le projectile 1 mis en place dans un tube de lancement 13.FIG. 2 represents in section along the plane AA of FIG. 1 the projectile 1 placed in a launching tube 13.

Comme cela apparait sur cette figure, le dispositif 6 comporte une surface de guidage externe 14 dont le diamètre est égal à celui du tube de lancement 13. Le dispositif améliore ainsi le guidage du projectile dans le tube de lancement.As shown in this figure, the device 6 has an external guide surface 14 whose diameter is equal to that of the launch tube 13. The device thus improves the guiding of the projectile in the launch tube.

Le fonctionnement du dispositif est le suivant.The operation of the device is as follows.

Lors du tir du projectile, les ailettes se trouvent fermement maintenues par le dispositif tout le long du parcours à l'intérieur du tube de lancement.When firing the projectile, the fins are firmly held by the device all along the path inside the launch tube.

A la sortie du tube l'écoulement aérodynamique pénètre dans les ouvertures 6a et 6b et exerce un effort sur les palettes 7a et 7b. Cet effort écarte les dispositifs 6 du corps la du projectile ce qui a pour effet d'entraîner les ailettes 4 par l'intermédiaire du fond 10a des rainures 10 et de la cloison 11.At the outlet of the tube, the aerodynamic flow enters the openings 6a and 6b and exerts a force on the pallets 7a and 7b. This effort separates the devices 6 from the body 1a of the projectile, which has the effect of driving the fins 4 via the bottom 10a of the grooves 10 and of the partition 11.

Toutes les ailettes sont ouvertes de façon symétrique cela principalement parce que, grâce au dispositif selon l'invention, l'effort appliqué à l'ailette est d'origine aérodynamique et il est maximal au début de l'ouverture. La symétrie est également favorisée par l'absence de vibrations de l'ailette obtenue grâce au calage transversal fourni par les profils de butée 12.All the fins are symmetrically open, mainly because, thanks to the device according to the invention, the force applied to the fin is of aerodynamic origin and it is maximum at the start of the opening. Symmetry is also favored by the absence of vibrations of the fin obtained thanks to the transverse setting provided by the stop profiles 12.

Le dispositif selon l'invention permet donc d'éviter les problèmes rencontrés avec les ressorts de déploiement connus dont les caractéristiques mécaniques risquent de se dégrader au cours du stockage du projectile.The device according to the invention therefore makes it possible to avoid the problems encountered with known deployment springs whose mechanical characteristics are liable to deteriorate during storage of the projectile.

Au delà d'un certain angle de déploiement, la résultante des efforts aérodynamiques ainsi que la force centrifuge qui s'exercent sur le dispositif 6 arrivent à vaincre les frottements entre l'ailette et la rainure 10 et entraînent la séparation du dispositif et de l'ailette.Beyond a certain deployment angle, the result of the aerodynamic forces as well as the centrifugal force which are exerted on the device 6 manage to overcome the friction between the fin and the groove 10 and cause the separation of the device and the 'fin.

Ainsi lors du déploiement, les dispositifs se trouvent automatiquement éjectés et ne viennent pas perturber le vol du projectile en occasionnant un freinage aérodynamique.Thus during deployment, the devices are automatically ejected and do not disturb the flight of the projectile by causing aerodynamic braking.

Il est possible de déterminer l'angle d'ouverture de l'ailette à partir duquel le dispositif se trouve éjecté en jouant sur les dimensions des surfaces de contact ailette/rainure (par exemple en donnant à la rainure une forme non parallèle aux faces latérales de l'ailette).It is possible to determine the angle of opening of the fin from which the device is ejected by varying the dimensions of the fin / groove contact surfaces (for example by giving the groove a shape which is not parallel to the lateral faces fin).

Il est possible également de déterminer l'angle auquel se produit l'éjection du dispositif en jouant sur la position de la paroi frontale 11 et/ou sur la forme de l'extrémité de l'ailette.It is also possible to determine the angle at which the device is ejected by varying the position of the front wall 11 and / or the shape of the end of the fin.

Dans ce cas à l'action de la force centrifuge s'ajoute celle du couple de basculement du dispositif par rapport à l'ailette qui est engendré par les forces aérodynamiques.In this case to the action of the centrifugal force is added that of the tilting torque of the device relative to the fin which is generated by the aerodynamic forces.

La figure 4 montre ainsi à titre d'exemple un dispositif dans lequel le fond 11 se trouve en retrait par rapport aux ouvertures d'entrée des canaux 6a, 6b.FIG. 4 thus shows by way of example a device in which the bottom 11 is set back relative to the inlet openings of the channels 6a, 6b.

La figure 5 représente schématiquement la partie arrière d'un projectile 1 équipé d'un dispositif de déploiement 15 selon un deuxième mode de réalisation de l'invention qui est destiné aux projectiles équipés d'un nombre pair d'ailettes.FIG. 5 schematically represents the rear part of a projectile 1 equipped with a deployment device 15 according to a second embodiment of the invention which is intended for projectiles equipped with an even number of fins.

Ce dispositif comprend une palette 7 destinée à recevoir l'écoulement aérodynamique qui apparait lors du tir le long du corps la du projectile entre la partie avant (repère AV) et la partie arrière (repère AR).This device comprises a pallet 7 intended to receive the aerodynamic flow which appears during the firing along the body of the projectile between the front part (mark AV) and the rear part (mark AR).

L'inclinaison de la palette par rapport à l'axe 8 du projectile est encore choisie telle que l'écoulement aérodynamique ait pour effet d'écarter le dispositif 15 du corps la du projectile.The inclination of the pallet relative to the axis 8 of the projectile is also chosen such that the aerodynamic flow has the effect of separating the device 15 from the body 1a of the projectile.

Les figures 7a, 7b et 7c représentent en détail ce dispositif de déploiement.Figures 7a, 7b and 7c show in detail this deployment device.

Il est lui aussi réalisé de préférence en matière plastique moulée.It is also preferably made of molded plastic.

La palette 7 est reliée à des parois latérales 8a et 8b qui se terminent par des pieds d'appui latéraux 9a et 9b.The pallet 7 is connected to side walls 8a and 8b which terminate in lateral support legs 9a and 9b.

Comme dans le mode de réalisation précédent, les parois latérales 8a, 8b sont planes et sensiblement parallèles aux surfaces latérales 4b,4c de l'ailette 4.As in the previous embodiment, the side walls 8a, 8b are planar and substantially parallel to the side surfaces 4b, 4c of the fin 4.

Ainsi le dispositif, après sa mise en place sur le projectile, se trouve conformé de façon à présenter, en regard de l'écoulement aérodynamique, un canal 15a dont l'ouverture d'entrée (disposée vers la partie avant AV du projectile) a une surface supérieure à celle de l'ouverture de sortie (orientée vers la partie arrière AR).Thus the device, after its installation on the projectile, is shaped so as to present, facing the aerodynamic flow, a channel 15a whose inlet opening (disposed towards the front part AV of the projectile) has a surface greater than that of the outlet opening (oriented towards the rear part AR).

Les pieds d'appui 9a,9b viennent en contact avec la surface externe du corps la du projectile, ils ont un profil cylindrique de diamètre égal à celui de ce corps.The support feet 9a, 9b come into contact with the external surface of the body la of the projectile, they have a cylindrical profile with a diameter equal to that of this body.

Ils portent chacun une surface d'entraînement latérale 16a,16b qui est destinée à recevoir l'appui d'une ailette 4.They each carry a lateral drive surface 16a, 16b which is intended to receive the support of a fin 4.

Chaque surface 16a,16b reçoit donc une ailette différente lorsque ces dernières se trouvent en position repliée le long du corps la du projectile.Each surface 16a, 16b therefore receives a different fin when the latter are in the folded position along the body la of the projectile.

Les pieds 9a, 9b portent également des zones de maintien 17a, 17b qui sont en contact chacune avec une surface latérale de l'ailette considérée.The feet 9a, 9b also carry holding zones 17a, 17b which are each in contact with a lateral surface of the fin considered.

Comme cela est plus particulièrement visible figure 6, trois dispositifs 15 selon l'invention permettent de déployer six ailettes.As is more particularly visible in FIG. 6, three devices 15 according to the invention make it possible to deploy six fins.

Chaque ailette se trouve maintenue latéralement d'un côté par une zone de maintien 17 portée par un des dispositifs 15 et de l'autre par un profil de butée 18 solidaire d'une bride 19 réalisée également en matière plastique et rendue solidaire du corps de projectile, par exemple par collage.Each fin is held laterally on one side by a holding zone 17 carried by one of the devices 15 and on the other by a stop profile 18 secured to a flange 19 also made of plastic and made integral with the body of projectile, for example by bonding.

Comme cela est visible sur la figure 5, les brides sont décalées axialement par rapport au dispositif, celà afin que les brides n'interdisent pas l'ouverture de l'ailette.As can be seen in FIG. 5, the flanges are offset axially relative to the device, this so that the flanges do not prevent the opening of the fin.

Les dimensions des dispositifs 15 et des brides 19 seront choisies de telle sorte qu'il n'y ait pas de jeu lors de la mise en place sur l'ailette.The dimensions of the devices 15 and of the flanges 19 will be chosen so that there is no play when it is placed on the fin.

Une telle disposition permet d'immobiliser les extrémités des ailettes ce qui évite les vibrations lors du tir et améliore le processus de déploiement et la stabilisation du projectile.Such an arrangement makes it possible to immobilize the ends of the fins, which prevents vibrations during shooting and improves the deployment process and the stabilization of the projectile.

Il serait néanmoins possible d'omettre les brides 19 et de ne conserver qu'un maintien unilatéral de l'ailette par la zone de maintien 17, le résultat obtenu serait cependant d'une efficacité moindre.It would nevertheless be possible to omit the flanges 19 and to keep only one-sided retention of the fin by the retention zone 17, the result obtained, however, being less effective.

Chaque dispositif 15 comporte enfin une languette arrière 20 qui est destinée à venir en appui contre une collerette 21 du projectile et qui constitue une butée axiale pour le dispositif.Each device 15 finally comprises a rear tongue 20 which is intended to come into abutment against a flange 21 of the projectile and which constitutes an axial stop for the device.

La languette permet également de localiser, au niveau de la collerette arrière et à égale distance de chaque ailette, le point de pivotement du dispositif. Une telle disposition assure une ouverture symétrique des deux ailettes par le dispositif.The tongue also makes it possible to locate, at the rear flange and at an equal distance from each fin, the pivot point of the device. Such an arrangement ensures symmetrical opening of the two fins by the device.

Il serait possible à titre de variante de remplacer cette languette par deux parois, chacune portée par un pied 9a,9b et perpendiculaire à la surface d'entraînement considérée 16a,16b. Ces parois venant en butée contre l'extrémité 4a de l'ailette lors du montage.It would be possible, as a variant, to replace this tongue with two walls, each carried by a foot 9a, 9b and perpendicular to the drive surface considered 16a, 16b. These walls abutting against the end 4a of the fin during assembly.

Comme dans la variante précédente, le dispositif 15 comporte une surface de guidage externe 14 dont le diamètre est égal à celui du tube de lancement 13. Le dispositif améliore ainsi le guidage du projectile dans le tube de lancement.As in the previous variant, the device 15 has an external guide surface 14 whose diameter is equal to that of the launch tube 13. The device thus improves the guiding of the projectile in the launch tube.

Le fonctionnement de ce mode de réalisation est analogue à celui du précédent.The operation of this embodiment is similar to that of the previous one.

Le dispositif de déploiement se trouve encore éjecté à partir d'un certain angle d'ouverture des ailettes.The deployment device is still ejected from a certain angle of opening of the fins.

Un avantage de ce mode de réalisation est qu'il permet d'éjecter très vite le dispositif ce qui réduit son action à une simple impulsion initiale sur les ailettes qui terminent ensuite leur ouverture par inertie et par l'effet de leur traînée propre.An advantage of this embodiment is that it makes it possible to eject the device very quickly, which reduces its action to a simple initial impulse on the fins which then terminate their opening by inertia and by the effect of their own drag.

L'éjection rapide du dispositif présente également l'avantage de limiter la vitesse angulaire de l'ailette en fin de course ce qui limite les rebonds de l'ailette et améliore la stabilisation du projectile.The rapid ejection of the device also has the advantage of limiting the angular speed of the fin at the end of the stroke, which limits the rebounds of the fin and improves the stabilization of the projectile.

En effet, la distance entre les extrémités de deux ailettes voisines augmente au cours de l'ouverture. Les ailettes se trouvent donc rapidement dégagées des surfaces d'entraînement 16a,16b et il est possible de déterminer précisément l'instant d'éjection du dispositif en jouant sur les dimensions des surfaces d'entraînement 16a,16b et notamment sur la longueur L (voir figures 6 et 7a).In fact, the distance between the ends of two neighboring fins increases during opening. The fins are therefore quickly released from the drive surfaces 16a, 16b and it is possible to precisely determine the instant of ejection of the device by adjusting the dimensions of the drive surfaces 16a, 16b and in particular over the length L ( see Figures 6 and 7a).

Un autre avantage de ce mode de réalisation est qu'il permet de réduire le nombre de dispositifs utilisés pour un projectile, donc le coût de réalisation.Another advantage of this embodiment is that it makes it possible to reduce the number of devices used for a projectile, and therefore the cost of production.

Enfin à titre de variante il serait possible de définir un dispositif de déploiement qui resterait solidaire de l'ailette même après déploiement. Un tel dispositif comprendrait par exemple une ou plusieurs palettes fixées aux parois latérales de chaque ailette.Finally, as a variant, it would be possible to define a deployment device which would remain integral with the fin even after deployment. Such a device would for example include one or more pallets fixed to the side walls of each fin.

Claims (10)

1-Dispositif de déploiement d'ailette de stabilisation (4) pour un projectile (1), caractérisé en ce qu'il comporte au moins une palette (7a,7b), rendue solidaire d'une ailette (4) par des moyens d'entraînement (10a,16a,16b), et orientée de façon à recevoir un écoulement aérodynamique lors du tir du projectile et à transmettre ainsi un effort résultant à l'ailette (4) afin de la déployer. 1- Deployment device for stabilization fin (4) for a projectile (1), characterized in that it comprises at least one pallet (7a, 7b), made integral with a fin (4) by means of drive (10a, 16a, 16b), and oriented so as to receive an aerodynamic flow during the firing of the projectile and thus to transmit a resulting force to the fin (4) in order to deploy it. 2-Dispositif selon la revendication 1, caractérisé en ce que les moyens d'entraînement (10a,16a,16b) de l'ailette (4) sont déverrouillables de façon à séparer le dispositif de déploiement et l'ailette à partir d'un certain angle d'ouverture de cette dernière. 2- Device according to claim 1, characterized in that the drive means (10a, 16a, 16b) of the fin (4) are unlockable so as to separate the deployment device and the fin from a certain opening angle of the latter. 3-Dispositif selon la revendication 2, caractérisé en ce qu'il comporte au moins deux palettes (7a,7b) séparées par une rainure (10) dans laquelle se positionne l'ailette (4), la rainure (10) comportant un fond (10a) sur lequel l'ailette (4) vient en appui lorsqu'elle se trouve en position repliée le long du corps de projectile (1) et qui constitue le moyen d'entraînement. 3- Device according to claim 2, characterized in that it comprises at least two pallets (7a, 7b) separated by a groove (10) in which is positioned the fin (4), the groove (10) having a bottom (10a) on which the fin (4) comes to bear when it is in the folded position along the projectile body (1) and which constitutes the drive means. 4-Dispositif selon la revendication 3, caractérisé en ce qu'il comporte une paroi frontale (11) fermant la rainure (10) au niveau d'une partie avant du dispositif et constituant une butée axiale pour l'extrémité de l'ailette (4). 4- Device according to claim 3, characterized in that it comprises a front wall (11) closing the groove (10) at a front part of the device and constituting an axial stop for the end of the fin ( 4). 5-Dispositif selon une des revendications 3 ou 4, caractérisé en ce qu'il comporte au moins deux pieds d'appui latéraux (9a,9b) qui sont en contact avec une surface externe du projectile (1) et qui sont maintenus par des profils de butée (12) portés par le projectile et disposés de façon à empêcher tout déplacement du dispositif suivant une direction perpendiculaire à une surface latérale (4b,4c) de l'ailette (4). 5- Device according to one of claims 3 or 4, characterized in that it comprises at least two lateral support feet (9a, 9b) which are in contact with an external surface of the projectile (1) and which are held by stop profiles (12) carried by the projectile and arranged so as to prevent any displacement of the device in a direction perpendicular to a lateral surface (4b, 4c) of the fin (4). 6-Dispositif selon la revendication 2, caractérisé en ce qu'il comporte au moins une palette (7) solidaire d'au moins deux surfaces d'entraînement latérales (16a, 16b), chacune de ces surfaces d'entraînement étant destinée à recevoir l'appui d'une ailette (4) différente du projectile (1) lorsque ces dernières se trouvent en position repliée le long du corps de projectile. 6- Device according to claim 2, characterized in that it comprises at least one pallet (7) integral with at least two lateral drive surfaces (16a, 16b), each of these drive surfaces being intended to receive the support of a fin (4) different from the projectile (1) when the latter are in the folded position along the projectile body. 7-Dispositif selon la revendication 6, caractérisé en ce qu'il comporte une languette (20) destinée à venir en appui contre une collerette (21) solidaire du projectile (1) et qui constitue une butée axiale pour le dispositif. 7- Device according to claim 6, characterized in that it comprises a tongue (20) intended to come into abutment against a flange (21) secured to the projectile (1) and which constitutes an axial stop for the device. 8-Dispositif selon la revendication 6, caractérisé en ce qu'il comporte au moins une paroi sensiblement perpendiculaire à chaque surface d'entraînement (16a,16b) et constituant une butée axiale pour l'extrémité de l'ailette (4) considérée. 8- Device according to claim 6, characterized in that it comprises at least one wall substantially perpendicular to each drive surface (16a, 16b) and constituting an axial stop for the end of the fin (4) considered. 9-Dispositif selon une des revendications 6 à 8, caractérisé en ce que chaque surface d'entraînement latérale (16a,16b) comporte une zone de maintien (17a,17b) d'une première surface latérale de l'ailette (4). 9- Device according to one of claims 6 to 8, characterized in that each lateral drive surface (16a, 16b) comprises a holding zone (17a, 17b) of a first lateral surface of the fin (4). 10-Dispositif selon une des revendications 1 à 9, caractérisé en ce qu'il comporte une surface de guidage externe (14) à profil circulaire et dont le diamètre est égal à celui d'un tube de lancement du projectile (1). 10- Device according to one of claims 1 to 9, characterized in that it comprises an external guide surface (14) with circular profile and whose diameter is equal to that of a projectile launching tube (1).
EP95401557A 1994-06-28 1995-06-28 Deploying device for a projectile wing Expired - Lifetime EP0690284B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9407953A FR2721702B1 (en) 1994-06-28 1994-06-28 Device for deploying a projectile fin.
FR9407953 1994-06-28

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EP0690284A1 true EP0690284A1 (en) 1996-01-03
EP0690284B1 EP0690284B1 (en) 1999-09-15

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EP (1) EP0690284B1 (en)
DE (1) DE69512146T2 (en)
ES (1) ES2138165T3 (en)
FR (1) FR2721702B1 (en)
IL (1) IL114383A (en)
ZA (1) ZA955302B (en)

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US12092436B2 (en) * 2021-09-03 2024-09-17 Raytheon Company Control surface restraining system for tactical flight vehicles

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Also Published As

Publication number Publication date
EP0690284B1 (en) 1999-09-15
DE69512146D1 (en) 1999-10-21
ES2138165T3 (en) 2000-01-01
US5685503A (en) 1997-11-11
ZA955302B (en) 1996-12-23
IL114383A (en) 1998-12-06
FR2721702A1 (en) 1995-12-29
IL114383A0 (en) 1995-10-31
FR2721702B1 (en) 1996-08-14
DE69512146T2 (en) 2000-01-27

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